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CN112177800A - Cooling structure for spiral wheel pair bearing of liquid rocket engine pump - Google Patents

Cooling structure for spiral wheel pair bearing of liquid rocket engine pump Download PDF

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Publication number
CN112177800A
CN112177800A CN202011050990.1A CN202011050990A CN112177800A CN 112177800 A CN112177800 A CN 112177800A CN 202011050990 A CN202011050990 A CN 202011050990A CN 112177800 A CN112177800 A CN 112177800A
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section
bearing
inlet
bearing cooling
cavity
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CN202011050990.1A
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CN112177800B (en
Inventor
于晴
王晓锋
李惠敏
毛凯
张聃
安康
李雨濛
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Xian Aerospace Propulsion Institute
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Xian Aerospace Propulsion Institute
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C37/00—Cooling of bearings

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

本发明一种液体火箭发动机泵螺旋轮对轴承冷却结构，包括：诱导轮(1)、螺旋轮(2)、轴承(3)、密封件(4)、轴端压紧螺母(5)、进口壳体(6)和轴(7)；进口壳体(6)，包括：入口段(67)和环形段(68)；环形段(68)，包括：出口段、过渡段和轴承冷却段；环形段(68)的过渡段内腔靠近轴承冷却段一侧设有通孔(63)；液体介质从入口段(67)进入进口壳体(6)，从出口段流出，在经过过渡段时，通过轴(7)带动螺旋轮(2)旋转，产生抽吸力，将经过过渡段的部分液体介质抽入过渡段内腔的通孔(63)中，流经轴承(3)再通过、螺旋轮(2)回流至过渡段，汇入出口，实现对轴承的冷却。本发明在保证轴承冷却流量的同时，简化发动机涡轮泵轴承冷却结构，并提高泵效率。

Figure 202011050990

The present invention is a liquid rocket engine pump screw wheel-to-bearing cooling structure, comprising: an inducer (1), a screw wheel (2), a bearing (3), a seal (4), a shaft end compression nut (5), an inlet housing (6) and shaft (7); inlet housing (6), including: inlet section (67) and annular section (68); annular section (68) including: outlet section, transition section and bearing cooling section; The inner cavity of the transition section of the annular section (68) is provided with a through hole (63) on the side close to the bearing cooling section; the liquid medium enters the inlet housing (6) from the inlet section (67) and flows out from the outlet section, and when passing through the transition section , drive the screw wheel (2) to rotate through the shaft (7), generate a suction force, and draw part of the liquid medium passing through the transition section into the through hole (63) of the inner cavity of the transition section, flow through the bearing (3), and then pass through, The helical wheel (2) returns to the transition section and merges into the outlet to cool the bearing. The invention simplifies the bearing cooling structure of the turbo pump of the engine while ensuring the cooling flow of the bearing, and improves the pump efficiency.

Figure 202011050990

Description

Cooling structure for spiral wheel pair bearing of liquid rocket engine pump
Technical Field
The invention relates to a cooling structure for a screw wheel pair bearing of a liquid rocket engine pump, and belongs to the technical field of cooling of turbo pumps of liquid rocket engines.
Background
The liquid rocket engine turbopump has high rotating speed and high pressure, the high-speed rotating friction of a bearing for supporting a turbopump rotor can cause temperature rise, the turbopump can generate large axial force and radial force which are borne by the bearing in the process from starting to shutting down of the engine, and the bearing needs to be continuously cooled in order to balance the generation of a large amount of frictional heat generated in the working process of the bearing.
The liquid rocket engine turbopump bearing is located in the pump chamber, generally adopts self propellant to cool, and the mode that usually adopts is: except for a main flow path of the propellant, an auxiliary flow path is specially arranged, a high-pressure medium is led out from an area with higher pressure in a pump cavity and returns to a main pump path after cooling a bearing, and the cooling mode not only loses the energy of the high-pressure medium and reduces the efficiency of the pump. In addition, more importantly, the auxiliary flow path in the pump is usually very complex, the product processing is difficult due to the general internal drainage, and corresponding pipelines are additionally arranged outside the pump shell under most conditions, so that the pump has the defects of complex structure and increased weight of an engine.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the cooling structure of the spiral wheel pair bearing of the liquid rocket engine pump is provided, the cooling flow of the bearing is ensured, the cooling structure of the turbine pump bearing of the engine is simplified, and the pump efficiency is improved.
The technical scheme of the invention is as follows: a liquid rocket engine pump helical gear pair bearing cooling structure, comprising: the device comprises an inducer (1), a spiral wheel (2), a bearing (3), a sealing element (4), a shaft end compression nut (5), an inlet shell (6) and a shaft (7);
an inlet housing (6) comprising: an inlet section (67) and an annular section (68);
an annular segment (68) comprising: the outlet section, the transition section and the bearing cooling section;
the inner cavity of the inlet section (67), the inner cavity of the transition section of the annular section and the inner cavity of the outlet section are jointly used as a main flow cavity;
the inner cavity of the outlet section is cylindrical, the inner cavity of the bearing cooling section is a bearing cooling cavity, the bearing cooling cavity is a multi-stage structure formed by sequentially arranging a plurality of cylinders with different diameters from small to large, one side of the smallest cylinder is the small end of the bearing cooling cavity, and one side of the largest cylinder is the large end of the bearing cooling cavity;
the spiral wheel (2) comprises a sleeve (21) and spiral teeth (22), and the spiral teeth (22) circumferentially surround the outer surface of the sleeve (21);
the inducer (1) is arranged in an outlet section inner cavity of an annular section (68) of the inlet shell (6);
the spiral wheel (2), the bearing (3) and the sealing element (4) are sequentially arranged in a bearing cooling section inner cavity of the annular section (68) of the inlet shell (6);
the inducer (1), the spiral wheel (2), the bearing (3), the sealing element (4) and the shaft end compression nut (5) are all assembled on the shaft (7), the shaft end compression nut (5) is arranged beside the sealing element (4), the shaft end compression nut (5) and the shaft (7) are screwed up in a torque manner, and the axial compression force ensures that the spiral wheel (2) rotates synchronously with the shaft (7);
the inducer (1) is connected with the shaft (7) through a spline;
a through hole (63) is formed in one side, close to the bearing cooling section, of the transition section inner cavity of the annular section (68), and the through hole (63) is communicated with the transition section inner cavity and the bearing cooling section inner cavity;
the through hole (63) is positioned between the bearing (3) and the sealing element (4) at the axial position of the bearing cooling section;
liquid medium enters an inlet shell (6) from an inlet section (67), passes through a main flow cavity, flows out from an outlet section, drives a spiral wheel (2) to rotate through a shaft (7) to generate suction force, partial liquid medium passing through a transition section is pumped into a through hole (63) of an inner cavity of the transition section, passes through the through hole (63) and reaches a space between a bearing (3) and a sealing element (4), flows through the bearing (3) to cool the bearing (3), takes away heat generated by the rotational friction of the bearing (3), flows back to the transition section through a spiral tooth (22), and is converged into the outlet section to cool the bearing;
and the sealing element (4) is used for blocking the liquid medium from flowing to the large end of the bearing cooling cavity of the bearing cooling section when reaching the space between the bearing (3) and the sealing element (4), and ensuring that all the liquid medium reaching the space between the bearing (3) and the sealing element (4) flows to the small end of the bearing cooling cavity of the bearing cooling section.
Preferably, the inlet section (67) is a convergent channel with a gradually changing cross section from large to small;
preferably, the inlet section (67) and the transition section in the inlet shell (6) are provided with first partition plates (61), and the first partition plates (61) penetrate through the inlet section and the transition section to reduce prerotation of the liquid medium.
Preferably, a second partition plate (62) is further arranged at the transition section in the inlet shell (6); the first partition plate (61) and the second partition plate (62) are flat plates, the planes of the second partition plate (62) and the first partition plate (61) are located on the same plane, and the central axis of the shaft (7) is also located in the plane of the second partition plate (62) and the first partition plate (61); the first partition plate (61) and the second partition plate (62) are respectively located on both sides of the central axis of the shaft (7).
Preferably, the radius clearance between the top of the spiral tooth (22) and the smallest diameter part of the bearing cooling cavity step cylindrical wall surface (65) of the bearing cooling section of the inlet shell (6) is 0.5-0.7 mm.
Preferably, the inlet shell (6) is of an axisymmetric structure, and the center line of the step cylindrical wall surface (65) of the bearing cooling cavity of the bearing cooling section in the annular section (68) of the inlet shell (6) and the center line of the cylindrical wall surface (66) of the outlet section of the inlet shell are collinear with the center line of the shaft (7).
Preferably, the offset distance l between the central line of the transition section of the annular section (68) of the inlet shell (6) and the central line of the shaft (7) is 40-45.5 cm.
Preferably, the inlet section (67) and the transition section inner cavity symmetric surface of the inlet shell (6) are provided with a first partition plate (61) and a second partition plate (62), the first partition plate (61) extends to the joint of the main flow cavity inner wall surface (64) and the bearing cooling cavity step cylindrical wall surface (65) of the transition section in the annular section (68) from the inlet of the inlet section (67) of the inlet shell (6), the second partition plate (62) is arranged on the other side of the symmetric surface of the inlet annular section (678) of the inlet shell (6), and the included angle between the second partition plate (62) and the first partition plate (61) is 180 degrees.
Preferably, two through holes (63) parallel to the symmetry plane are formed in the inner wall surface (64) of the main flow cavity of the transition section of the inlet shell (6), and the through holes (63) are symmetrical about the symmetry plane and penetrate through the inner wall surface (64) of the main flow cavity of the transition section and the step cylindrical wall surface (65) of the bearing cooling cavity of the bearing cooling section.
Preferably, two ends of the outer diameter of the sleeve (21) are cylindrical sections, one end with a small diameter is a small end of the sleeve (21), the other end with a large diameter is a large end of the sleeve (21), the middle of the two cylindrical sections is in conical transition, and the small end of the sleeve is matched with the end face of the bearing.
Preferably, the helical teeth (22) are uniformly distributed along the circumferential direction of the outer surface of the small-end cylindrical section of the sleeve (21), the rotation direction of the helical teeth (22) is right-handed, the cross section of the helical teeth (22) is trapezoidal, the number of the helical teeth (22) is 6-10, the axial length of the helical teeth (22) is 14-16.5 mm, the thread pitch of the helical teeth (22) is 65-70 mm, the tooth height of the helical teeth (22) is 3-4 mm, and the tooth top width of the helical teeth (22) is 0.8-1 mm.
Preferably, the inner diameter of the sleeve (21) is divided into three cylindrical sections, the inner diameter of the large end of the sleeve (21) is slightly larger than that of the small end of the sleeve (21), the inner diameter of the middle section is the largest, and meanwhile, the diameter of the shaft (7) at the large end matching part of the sleeve (21) is slightly larger than that of the shaft (7) at the small end matching part of the sleeve (21).
Compared with the prior art, the invention has the advantages that:
(1) the invention solves the problems of the traditional structure, and provides a bearing cooling loop structure, which is used for cooling a bearing in a pump cavity, simplifying the external structure of an engine and lightening the weight of the engine.
(2) The structure of the cooling bearing is a simple and reliable bearing cooling loop structure, a helical wheel is arranged in a flow path in a pump, the helical wheel and a shaft rotate synchronously, the pumping action is realized, the circulation power is provided for a bearing cooling auxiliary path, two through holes parallel to a symmetrical plane are formed in the inner wall surface of a main flow cavity of an inlet shell transition section, the through holes penetrate through the inner wall surface of the main flow cavity of the transition section and the step cylindrical wall surface of the bearing cooling cavity, a medium is introduced from the two through holes of the inlet shell by using the pumping action of the helical wheel, the cooling bearing is pressurized by the helical wheel and returns to an inducer inlet, a cooling flow path is completely sealed in the pump, a pipeline does not need to be additionally arranged outside the pump, the structure is simple, and the weight of an engine. More importantly, the bearing is cooled by adopting a low-pressure medium, so that the energy loss of fluid is reduced, and the pump efficiency is improved.
(3) The spiral wheel is right-handed, the flowing direction of a liquid medium is introduced from the through hole in the inner cavity of the transition section of the inlet shell, the liquid medium sequentially flows through the bearing and the spiral wheel and then returns to the inlet of the inducer, the axial position of the opening of the through hole on the step cylindrical wall surface of the bearing cooling cavity is positioned between the bearing and the sealing element, the pressure of the liquid medium at the outlet of the through hole is further reduced compared with the pressure of the inlet at the inlet section of the inlet shell, namely, the pressure of the medium to be sealed by the sealing element is reduced, the pressure difference borne by the sealing.
(4) According to the invention, by reasonably setting parameters such as the number of teeth, the axial length and the screw pitch of the spiral teeth, the number and the aperture of the through holes and the like, the flow of the cooling bearing can be accurately controlled, and the reliable work of the bearing is ensured.
Drawings
FIG. 1 is a schematic view of a helical wheel cooling bearing arrangement of the present invention;
FIG. 2 is a block diagram of the spiral wheel of FIG. 1;
FIG. 3 is a block diagram of the inlet housing of FIG. 1;
FIG. 4 is a right side view of the inlet housing of FIG. 3;
FIG. 5 is a three-dimensional view of the inlet housing ring segment of FIG. 3.
In the figure: 1-inducer; 2, a spiral wheel; 3, a bearing; 4-a sealing member; 5, pressing a nut at the shaft end; 6-inlet housing; 7-axis; 21-a sleeve; 22-helical teeth; 61 — a first separator; 62-a second separator; 63-a through hole; 64-inner wall surface of main flow cavity; 65-bearing cooling chamber step cylindrical wall surface; 66-cylindrical wall surface of outlet section of inlet housing; 67 — an inlet section; 68-ring segment.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention relates to a cooling structure for a bearing of a spiral wheel pair of a liquid rocket engine pump, which comprises: the device comprises an inducer (1), a spiral wheel (2), a bearing (3), a sealing element (4), a shaft end compression nut (5), an inlet shell (6) and a shaft (7); an inlet housing (6) comprising: an inlet section (67) and an annular section (68); an annular segment (68) comprising: the outlet section, the transition section and the bearing cooling section; a through hole (63) is formed in one side, close to the bearing cooling section, of the transition section inner cavity of the annular section (68); liquid medium enters the inlet shell (6) from the inlet section (67) and flows out from the outlet section, when the liquid medium passes through the transition section, the spiral wheel (2) is driven to rotate through the shaft (7), suction force is generated, part of the liquid medium passing through the transition section is pumped into the through hole (63) of the inner cavity of the transition section, and the liquid medium flows through the bearing (3) and then flows back to the transition section through the spiral wheel (2) and then flows into the outlet, so that the cooling of the bearing is realized. The invention can simplify the cooling structure of the turbine pump bearing of the engine and improve the pump efficiency while ensuring the cooling flow of the bearing.
The invention relates to a cooling structure of a spiral wheel bearing of a liquid rocket engine pump, which is used for a flow loop in a pump structure, wherein the pressure of a cooling bearing medium before the cooling bearing medium is introduced into a bearing meets the cooling flow of the bearing, and must be within the range of the sealing capability of a sealing element, the pressure of the cooling bearing medium cannot be too low or too high, the cooling bearing medium is generally introduced out from the position of an inducer, which is close to an outlet, if the introduction position of the cooling bearing medium in the pump is limited by the pump structure and the cooling of the bearing cannot be realized in the pump, the scheme of the invention is adopted, through reasonably setting the parameters of the spiral wheel and utilizing the suction effect, a through hole is arranged on the wall surface of a main flow cavity of the inlet shell of the pump, a low-pressure medium is introduced to cool the bearing, the cooling flow of the bearing is accurately controlled, and the medium pressure that the sealing member needs to seal further reduces than pump inlet casing entry section for seal assembly operating mode is good, and the reliability improves.
As shown in figure 1, the spiral wheel pair bearing cooling structure of the liquid rocket engine pump comprises an inducer (1), a spiral wheel (2), a bearing (3), a sealing element (4), a shaft end gland nut (5), an inlet shell (6) and a shaft (7), wherein the inducer (1), the spiral wheel (2), the bearing (3), the sealing element (4) and the shaft end gland nut (5) are all assembled on the shaft (7), the shaft end gland nut (5) is arranged beside the sealing element (4), the shaft end gland nut (5) is screwed with the shaft (7) in a torque manner, and the axial pressing force ensures that the spiral wheel (2) rotates synchronously with the shaft (7). The inducer (1) is connected with the shaft (7) through a spline. And the sealing element (4) is used for blocking the liquid medium from flowing to the large end of the bearing cooling cavity of the bearing cooling section when reaching the space between the bearing (3) and the sealing element (4), and ensuring that all the liquid medium reaching the space between the bearing (3) and the sealing element (4) flows to the small end of the bearing cooling cavity of the bearing cooling section.
As shown in fig. 4, the inlet housing (6) has an axisymmetric structure, and the inlet housing 6 is processed by investment casting or 3D printing and is made of a high-strength stainless steel material. The inlet shell (6) comprises an inlet section (67) and an annular section (68), the inlet section (67) is a contraction channel with a cross section gradually changing from large to small, the offset l between the central line of the transition section of the annular section (68) of the inlet shell (6) and the central line of the shaft (7) is preferably 40-45.5 cm, and the performance of a spiral wheel of a liquid rocket engine pump on a bearing cooling structure is further improved.
As shown in fig. 5, the ring segment (68) includes an outlet segment, a transition segment and a bearing cooling segment, the transition segment inner cavity and the outlet segment inner cavity of the inlet segment (67) inner cavity and the ring segment (68) are jointly used as a main flow cavity, the outlet segment inner cavity is cylindrical, the bearing cooling segment inner cavity is a bearing cooling cavity, the bearing cooling cavity is a multi-stage structure formed by sequentially arranging a plurality of cylinders with different diameters from small to large according to the diameter, the small end of the bearing cooling cavity is arranged on one side of the smallest cylinder, and the large end of the bearing cooling cavity is arranged on one side of the largest cylinder. The inducer (1) is arranged in an outlet section inner cavity of an annular section (68) of the inlet shell (6). The spiral wheel (2), the bearing (3) and the sealing element (4) are sequentially arranged in a bearing cooling section inner cavity of the annular section (68) of the inlet shell (6);
as shown in fig. 3, the inlet section (67) and the transition section in the inlet casing (6) are provided with a first partition plate (61), and the first partition plate (61) penetrates through the inlet section and the transition section. The transition section in the inlet shell (6) is also provided with a second clapboard (62). The first partition plate (61) and the second partition plate (62) are flat plates, the planes of the second partition plate (62) and the first partition plate (61) are located on the same plane, and the central axis of the shaft (7) is also located in the plane of the second partition plate (62) and the first partition plate (61); the first partition plate (61) and the second partition plate (62) are respectively located on both sides of the central axis of the shaft (7). The arrangement of the first partition (61) and the second partition (62) can increase the rigidity of the inlet shell (6), reduce deformation and reduce the pre-rotation effect of the fluid. The center lines of the bearing cooling cavity step cylindrical wall surface (65) of the bearing cooling section in the annular section (68) of the inlet shell (6) and the cylindrical wall surface (66) of the outlet section of the inlet shell are collinear with the center line of the shaft (7). Two through holes (63) parallel to the symmetry plane are formed in one side, close to the bearing cooling section, of the inner wall surface of the main flow cavity of the transition section of the annular section (68), and the through holes (63) are symmetrical relative to the symmetry plane and penetrate through the inner wall surface (64) of the main flow cavity of the transition section and the step cylindrical wall surface (65) of the bearing cooling cavity of the bearing cooling section. The through hole (63) is communicated with the inner cavity of the transition section and the inner cavity of the bearing cooling section. The through hole (63) is positioned between the bearing (3) and the sealing element (4) at the axial position of the bearing cooling section;
the preferred scheme is as follows: as shown in fig. 2, the helical wheel (2) comprises a sleeve (21) and helical teeth (22), and is made of a lighter aluminum alloy material and integrally machined by adopting a forging piece or a bar material. In order to meet the assembly requirement of the bearing 3, two ends of the outer diameter of the sleeve (21) are cylindrical sections, the end with the small diameter is the small end of the sleeve (21), the end with the large diameter is the large end of the sleeve (21), the middle of the two cylindrical sections is in conical transition, and the small end of the sleeve is matched with the end face of the bearing. The spiral teeth (22) circumferentially surround the outer surface of the sleeve (21), and the spiral teeth (22) are circumferentially and uniformly distributed along the outer surface of the small-end cylindrical section of the sleeve (21). In order to accurately control the cooling flow of the bearing, the radius clearance between the top of the spiral tooth (22) and the minimum diameter position of the step cylindrical wall surface (65) of the bearing cooling cavity of the bearing cooling section of the inlet shell (6) is preferably 0.5-0.7 mm. The spiral direction of helical tooth (22) is the dextrorotation, the cross sectional shape of helical tooth (22) is trapezoidal, the number of teeth of helical tooth (22) is preferred 6 ~ 10, the axial length of helical tooth (22) is preferred 14 ~ 16.5mm, the pitch of helical tooth (22) is preferred 65 ~ 70mm, the tooth height of helical tooth (22) is preferred 3 ~ 4mm, the tooth top width of helical tooth (22) is preferred 0.8 ~ 1mm, the performance of liquid rocket engine pump spiral wheel to bearing cooling structure has further been improved. The inner diameter of the sleeve (21) is divided into three cylindrical sections, the inner diameter of the large end of the sleeve (21) is preferably phi 55.2mm, the inner diameter of the small end side of the sleeve (21) is preferably phi 55mm, the inner diameter of the middle section is phi 56mm, the inner diameter of the large end of the sleeve (21) is slightly larger than the inner diameter of the small end of the sleeve (21), the inner diameter of the middle section is the largest, the length of a matching positioning surface of the sleeve (21) and the shaft (7) is shortened, the size machining precision is guaranteed, meanwhile, the diameter of the shaft (7) at the large end matching position of the sleeve (21) is slightly larger than the diameter of the shaft (7).
Liquid medium enters an inlet shell (6) from an inlet section (67), passes through a main flow cavity, flows out from an outlet section, drives a spiral wheel (2) to rotate through a shaft (7) to generate suction force, partial liquid medium passing through a transition section is pumped into a through hole (63) of an inner cavity of the transition section, the liquid medium passes through the through hole (63) and reaches a position between a bearing (3) and a sealing element (4), flows through the bearing (3) to cool the bearing (3), takes away heat generated by the rotational friction of the bearing (3), and then flows back to the transition section through spiral teeth (22) to be converged into the outlet section, so that the cooling of the bearing is realized, a cooling flow path of the bearing (3) is completely sealed in a pump, the external structure of the engine is simplified, the weight of the engine is reduced, the energy loss of the medium is reduced, and the pump efficiency. In addition, the liquid medium pressure at the outlet of the through hole is further reduced compared with the inlet pressure of the inlet section of the inlet shell, namely, the medium pressure required to be sealed by the sealing element is reduced, and the pressure difference borne by the sealing element is reduced, so that the working condition of the sealing element is good, and the reliability is improved.
The invention realizes the further preferable proposal of accurate control of the flow of the spiral wheel cooling bearing: let q be the flow passing through the helical wheel, omega be the rotation angular velocity of the helical wheel, s be the pitch, ρ be the medium density, F be the helical wheel inlet flow area, D be the helical wheel tip diameter, D be the product of the through-hole flow resistance coefficient mu 1 and the flow area A1, B be the helical wheel flow parameterThe product of the flow resistance coefficient mu 2 of the large end side of the spiral wheel sleeve and the flow area B1 of the large end side of the spiral wheel sleeve, the flow q meets the preferable constraint condition:
Figure BDA0002709543250000091
wherein g is the gravity acceleration, pi is the circumferential rate, and the accurate control of the helical wheel cooling bearing flow can be realized by adjusting the structural parameters of the helical wheel and the through hole.
The invention adopts the scheme that the flow of the helical wheel measured after the test of a certain liquid rocket engine is 2% of the designed value of the cooling flow required by the bearing, the lift of the helical wheel is 1% of the designed value, the test is consistent with the designed value, and the bearing and the sealing element are intact after the decomposition.
The invention relates to a bearing cooling loop structure, which completes the cooling of a bearing in a pump cavity, simplifies the external structure of an engine, lightens the weight of the engine, arranges a spiral wheel in a flow path, realizes the extraction of a low-pressure medium from a transition section with lower pressure in the pump by utilizing the suction action of the spiral wheel, and converges the low-pressure medium into an outlet section of a main pump path after the cooling of the bearing, thereby reducing the energy loss of the medium and improving the pump efficiency.
The structure of the cooling bearing is a simple and reliable bearing cooling loop structure, a helical wheel is arranged in a flow path in a pump, the helical wheel and a shaft rotate synchronously, the pumping action is realized, the circulation power is provided for a bearing cooling auxiliary path, two through holes parallel to a symmetrical plane are formed in the inner wall surface of a main flow cavity of an inlet shell transition section, the through holes penetrate through the inner wall surface of the main flow cavity of the transition section and the step cylindrical wall surface of the bearing cooling cavity, a medium is introduced from the two through holes of the inlet shell by using the pumping action of the helical wheel, the cooling bearing is pressurized by the helical wheel and returns to an inducer inlet, a cooling flow path is completely sealed in the pump, a pipeline does not need to be additionally arranged outside the pump, the structure is simple, and the weight of an engine. More importantly, the bearing is cooled by adopting a low-pressure medium, so that the energy loss of fluid is reduced, and the pump efficiency is improved.
The spiral wheel is right-handed, the flowing direction of a liquid medium is introduced from the through hole in the inner cavity of the transition section of the inlet shell, the liquid medium sequentially flows through the bearing and the spiral wheel and then returns to the inlet of the inducer, the axial position of the opening of the through hole on the step cylindrical wall surface of the cooling cavity of the bearing is positioned between the bearing and the sealing element, the pressure of the liquid medium at the outlet of the through hole is further reduced compared with the pressure of the inlet at the inlet section of the inlet shell, namely, the pressure of the medium to be sealed by the sealing element is reduced, and the pressure difference borne by the sealing element is reduced, so that the working condition of the sealing element is good, and the reliability is improved.

Claims (10)

1.一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于包括：诱导轮(1)、螺旋轮(2)、轴承(3)、密封件(4)、轴端压紧螺母(5)、进口壳体(6)和轴(7)；1. A liquid rocket engine pump screw wheel pair bearing cooling structure is characterized in that comprising: inducer wheel (1), screw wheel (2), bearing (3), seal (4), shaft end compression nut (5) ), inlet housing (6) and shaft (7); 进口壳体(6)，包括：入口段(67)和环形段(68)；an inlet housing (6), comprising: an inlet section (67) and an annular section (68); 环形段(68)，包括：出口段、过渡段和轴承冷却段；an annular section (68), including: an outlet section, a transition section and a bearing cooling section; 入口段(67)内腔和环形段的过渡段内腔以及出口段内腔共同作为主流腔；The inner cavity of the inlet section (67), the inner cavity of the transition section of the annular section and the inner cavity of the outlet section together serve as the main flow cavity; 出口段内腔为圆柱形，轴承冷却段内腔为轴承冷却腔，轴承冷却腔为多个直径不同的圆柱形按直径从小到大依次排列形成的多级结构，最小的圆柱一侧为轴承冷却腔的小端，最大的圆柱一侧为轴承冷却腔的大端，；The inner cavity of the outlet section is cylindrical, the inner cavity of the bearing cooling section is the bearing cooling cavity, and the bearing cooling cavity is a multi-stage structure formed by a plurality of cylinders with different diameters arranged in order from small to large in diameter, and the side of the smallest cylinder is the bearing cooling The small end of the cavity, the largest cylindrical side is the big end of the bearing cooling cavity; 所述螺旋轮(2)包括套筒(21)和螺旋齿(22)，所述螺旋齿(22)沿周向环绕于套筒(21)外表面；The helical wheel (2) comprises a sleeve (21) and helical teeth (22), and the helical teeth (22) surround the outer surface of the sleeve (21) in the circumferential direction; 诱导轮(1)置于进口壳体(6)的环形段(68)的出口段内腔内；The inducer (1) is placed in the inner cavity of the outlet section of the annular section (68) of the inlet housing (6); 所述螺旋轮(2)、轴承(3)和密封件(4)依次排列置于进口壳体(6)的环形段(68)的轴承冷却段内腔内；The helical wheel (2), the bearing (3) and the seal (4) are arranged in sequence and placed in the inner cavity of the bearing cooling section of the annular section (68) of the inlet housing (6); 诱导轮(1)、螺旋轮(2)、轴承(3)、密封件(4)和轴端压紧螺母(5)均装配在轴(7)上，轴端压紧螺母(5)置于密封件(4)旁，轴端压紧螺母(5)与轴(7)力矩拧紧，轴向压紧力保证螺旋轮(2)随轴(7)同步转动；The inducer (1), the screw wheel (2), the bearing (3), the seal (4) and the shaft end compression nut (5) are all assembled on the shaft (7), and the shaft end compression nut (5) is placed on the shaft (7). Next to the seal (4), the shaft end pressing nut (5) is torqued to the shaft (7), and the axial pressing force ensures that the screw wheel (2) rotates synchronously with the shaft (7); 诱导轮(1)和轴(7)通过花键连接；The inducer (1) and the shaft (7) are connected by splines; 环形段(68)的过渡段内腔靠近轴承冷却段一侧设有通孔(63)，通孔(63)连通过渡段内腔与轴承冷却段内腔；The inner cavity of the transition section of the annular section (68) is provided with a through hole (63) on the side close to the bearing cooling section, and the through hole (63) communicates with the inner cavity of the transition section and the inner cavity of the bearing cooling section; 通孔(63)在轴承冷却段的轴向位置处于轴承(3)与密封件(4)之间；The through hole (63) is located between the bearing (3) and the seal (4) at the axial position of the bearing cooling section; 液体介质从入口段(67)进入进口壳体(6)，经过主流腔，从出口段流出，通过轴(7)带动螺旋轮(2)旋转，产生抽吸力，将经过过渡段的部分液体介质抽入过渡段内腔的通孔(63)中，液体介质穿过通孔(63)，到达轴承(3)与密封件(4)之间，流经轴承(3)对轴承(3)进行冷却，带走轴承(3)旋转摩擦产生的热量，再通过螺旋齿(22)回流至过渡段，汇入出口段，实现对轴承的冷却；The liquid medium enters the inlet housing (6) from the inlet section (67), passes through the main flow cavity, flows out from the outlet section, and drives the screw wheel (2) to rotate through the shaft (7) to generate a suction force, and part of the liquid passing through the transition section is drawn. The medium is drawn into the through hole (63) in the inner cavity of the transition section, the liquid medium passes through the through hole (63), reaches between the bearing (3) and the seal (4), and flows through the bearing (3) to the bearing (3) Cooling is carried out to take away the heat generated by the rotating friction of the bearing (3), and then return to the transition section through the helical teeth (22), and merge into the outlet section to achieve cooling of the bearing; 密封件(4)，用于阻断液体介质在到达轴承(3)与密封件(4)之间时向轴承冷却段的轴承冷却腔的大端流动，保证到达轴承(3)与密封件(4)之间的全部液体介质流向轴承冷却段的轴承冷却腔的小端。The seal (4) is used to block the flow of the liquid medium to the large end of the bearing cooling cavity of the bearing cooling section when it reaches between the bearing (3) and the seal (4), so as to ensure that the liquid medium reaches the bearing (3) and the seal (4). 4) All the liquid medium in between flows to the small end of the bearing cooling cavity of the bearing cooling section. 2.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：入口段(67)为横截面从大到小逐渐变化的收缩通道。2. A liquid rocket engine pump screw wheel pair bearing cooling structure according to claim 1, characterized in that: the inlet section (67) is a constricted channel whose cross section changes gradually from large to small. 3.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：所述进口壳体(6)内的入口段(67)和过渡段设有第一隔板(61)，第一隔板(61)贯穿入口段和过渡段，减小液体介质的预旋。3. A liquid rocket engine pump screw wheel pair bearing cooling structure according to claim 1, characterized in that: the inlet section (67) and the transition section in the inlet housing (6) are provided with a first partition plate (61), the first partition plate (61) penetrates the inlet section and the transition section to reduce the pre-swirl of the liquid medium. 4.根据权利要求3所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：进口壳体(6)内的过渡段还设有第二隔板(62)；第一隔板(61)和第二隔板(62)均为平板，第二隔板(62)与第一隔板(61)所在的平面位于同一平面，且轴(7)的中心轴线也位于第二隔板(62)与第一隔板(61)所在的平面内；第一隔板(61)与第二隔板(62)分别位于轴(7)的中心轴线的两侧。4. A liquid rocket engine pump screw wheel pair bearing cooling structure according to claim 3, characterized in that: the transition section in the inlet housing (6) is also provided with a second partition plate (62); Both the plate (61) and the second partition (62) are flat plates, the second partition (62) and the plane where the first partition (61) is located are located on the same plane, and the central axis of the shaft (7) is also located in the second partition. The partition plate (62) and the first partition plate (61) are in the plane; the first partition plate (61) and the second partition plate (62) are respectively located on both sides of the central axis of the shaft (7). 5.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：所述螺旋齿(22)顶部与进口壳体(6)轴承冷却段的轴承冷却腔台阶圆柱壁面(65)直径最小处半径间隙为0.5～0.7mm。5. A liquid rocket engine pump screw wheel-to-bearing cooling structure according to claim 1, characterized in that: the top of the helical teeth (22) and the bearing cooling cavity step cylinder of the bearing cooling section of the inlet housing (6) The radius gap at the minimum diameter of the wall surface (65) is 0.5-0.7 mm. 6.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：所述进口壳体(6)为轴对称结构，进口壳体(6)环形段(68)中轴承冷却段的轴承冷却腔台阶圆柱壁面(65)、进口壳体出口段圆柱壁面(66)中心线与轴(7)的中心线共线。6. A liquid rocket engine pump screw wheel-to-bearing cooling structure according to claim 1, characterized in that: the inlet casing (6) is an axisymmetric structure, and the inlet casing (6) annular segment (68) The centerline of the stepped cylindrical wall surface (65) of the bearing cooling cavity in the middle bearing cooling section and the centerline of the cylindrical wall surface (66) of the outlet section of the inlet casing and the centerline of the shaft (7) are collinear. 7.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：所述进口壳体(6)环形段(68)的过渡段中心线与轴(7)中心线偏距l为40～45.5cm。7. A liquid rocket engine pump screw wheel pair bearing cooling structure according to claim 1, characterized in that: the centerline of the transition section of the annular segment (68) of the inlet casing (6) and the center of the shaft (7) Line offset distance l is 40 ~ 45.5cm. 8.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：进口壳体(6)入口段(67)和过渡段内腔对称面设有第一隔板(61)和第二隔板(62)，第一隔板(61)从进口壳体(6)入口段(67)入口延伸至环形段(68)中过渡段的主流腔内壁面(64)与轴承冷却腔台阶圆柱壁面(65)交接处，第二隔板(62)置于进口壳体(6)入口环形段(678)对称面另一侧，与第一隔板(61)夹角为180°。8. A liquid rocket engine pump screw wheel-to-bearing cooling structure according to claim 1, characterized in that: the inlet housing (6) inlet section (67) and the inner cavity symmetry plane of the transition section are provided with a first partition plate (61) and a second partition (62), the first partition (61) extends from the inlet of the inlet casing (6) inlet section (67) to the inner wall surface (64) of the main flow chamber of the transition section in the annular section (68). At the junction with the stepped cylindrical wall surface (65) of the bearing cooling chamber, the second partition plate (62) is placed on the other side of the symmetrical plane of the inlet annular segment (678) of the inlet casing (6), at an angle with the first partition plate (61). is 180°. 9.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：所述进口壳体(6)过渡段的主流腔内壁面(64)上开设有两个平行于对称面的通孔(63)，所述通孔(63)关于对称面对称，贯穿过渡段的主流腔内壁面(64)和轴承冷却段的轴承冷却腔台阶圆柱壁面(65)。9. A liquid rocket engine pump screw wheel pair bearing cooling structure according to claim 1, characterized in that: the inner wall surface (64) of the main flow cavity of the transition section of the inlet casing (6) is provided with two parallel The through hole (63) on the symmetry plane is symmetrical about the symmetry plane, and penetrates the inner wall surface (64) of the main flow cavity of the transition section and the cylindrical wall surface (65) of the bearing cooling cavity of the bearing cooling section. 10.根据权利要求1所述的一种液体火箭发动机泵螺旋轮对轴承冷却结构，其特征在于：所述套筒(21)外径两端为圆柱段，直径小的一端为套筒(21)的小端，直径大的一端为套筒(21)的大端，两圆柱段中间锥形过渡，套筒的小端与轴承端面配合。10. A liquid rocket engine pump screw wheel pair bearing cooling structure according to claim 1, characterized in that: the outer diameter ends of the sleeve (21) are cylindrical sections, and the end with a smaller diameter is the sleeve (21). ), the end with the larger diameter is the large end of the sleeve (21), the middle of the two cylindrical sections is conical in transition, and the small end of the sleeve is matched with the end face of the bearing.
CN202011050990.1A 2020-09-29 2020-09-29 Cooling structure for spiral wheel pair bearing of liquid rocket engine pump Expired - Fee Related CN112177800B (en)

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1226641A (en) * 1998-02-17 1999-08-25 鄢平安 High speed centrifugal pump
JP2008038770A (en) * 2006-08-07 2008-02-21 Nsk Ltd Pump device
CN102588061A (en) * 2011-01-12 2012-07-18 福特环球技术公司 Supercharged liquid-cooled internal combustion engine
CN104421214A (en) * 2013-08-29 2015-03-18 江苏太阳宝新能源有限公司 High-temperature pump bearing cooling device
CN111140509A (en) * 2019-11-27 2020-05-12 西安航天动力研究所 Coaxial turbine pump structure of liquid oxygen kerosene engine
CN111140401A (en) * 2019-12-18 2020-05-12 西安航天动力研究所 Spherical turbine shell for liquid rocket engine and turbopump

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1226641A (en) * 1998-02-17 1999-08-25 鄢平安 High speed centrifugal pump
JP2008038770A (en) * 2006-08-07 2008-02-21 Nsk Ltd Pump device
CN102588061A (en) * 2011-01-12 2012-07-18 福特环球技术公司 Supercharged liquid-cooled internal combustion engine
CN104421214A (en) * 2013-08-29 2015-03-18 江苏太阳宝新能源有限公司 High-temperature pump bearing cooling device
CN111140509A (en) * 2019-11-27 2020-05-12 西安航天动力研究所 Coaxial turbine pump structure of liquid oxygen kerosene engine
CN111140401A (en) * 2019-12-18 2020-05-12 西安航天动力研究所 Spherical turbine shell for liquid rocket engine and turbopump

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