CN118815555A - A turbine bearing casing support structure for an aircraft engine - Google Patents
A turbine bearing casing support structure for an aircraft engine Download PDFInfo
- Publication number
- CN118815555A CN118815555A CN202411033437.5A CN202411033437A CN118815555A CN 118815555 A CN118815555 A CN 118815555A CN 202411033437 A CN202411033437 A CN 202411033437A CN 118815555 A CN118815555 A CN 118815555A
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- Prior art keywords
- bearing
- load
- bearing rod
- bidirectional
- rod
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
本申请提供了一种航空发动机涡轮承力机匣支撑结构，包括：内涵承力环、外涵承力环、双向承力杆、承力杆安装座和承力杆拉紧螺钉；双向承力杆包含主体段、位于主体段两端的连接段以及位于连接段内的球窝，球窝内有安装关节球头；内涵承力环上设有轴承座，外涵承力环上设有安装座，双向承力杆的一端通过关节球头及连接件安装到内涵承力环的轴承座上，双向承力杆的另一端通过关节球头及连接件安装到承力杆联接座上，承力杆联接座插入至外涵承力环的安装座内，并通过径向设置的承力杆拉紧螺钉安装在安装座上。本申请实现了通过内涵承力环向外涵承力环直接传力，满足发动机不同工作状态下对承拉、承拉双向传力的功能需求，改善了承力框架的受力条件。
The present application provides a support structure for a turbine bearing casing of an aircraft engine, comprising: an inner bearing ring, an outer bearing ring, a bidirectional bearing rod, a bearing rod mounting seat and a bearing rod tensioning screw; the bidirectional bearing rod comprises a main section, a connecting section at both ends of the main section and a ball socket in the connecting section, and a joint ball head is installed in the ball socket; a bearing seat is provided on the inner bearing ring, and a mounting seat is provided on the outer bearing ring. One end of the bidirectional bearing rod is installed on the bearing seat of the inner bearing ring through a joint ball head and a connecting piece, and the other end of the bidirectional bearing rod is installed on the bearing rod connecting seat through a joint ball head and a connecting piece. The bearing rod connecting seat is inserted into the mounting seat of the outer bearing ring, and is installed on the mounting seat through a radially arranged bearing rod tensioning screw. The present application realizes direct force transmission from the inner bearing ring to the outer bearing ring, meets the functional requirements of tension and tension bidirectional force transmission under different working conditions of the engine, and improves the force conditions of the bearing frame.
Description
Technical Field
The application belongs to the field of aero-engines, and particularly relates to a turbine bearing casing supporting structure of an aero-engine.
Background
The turbine bearing casing assembly of the aeroengine is an important force transmission component of the engine and is used for transmitting the acting force of a rotor acting on a bearing point bearing of the bearing casing to the outer culvert casing, and simultaneously keeping the concentricity of the inner culvert casing and the outer culvert casing and the concentricity of an inner culvert rotor and a stator. The typical force transmission path of the bearing case assembly is: bearing pedestal, bearing frame, short pull rod, and outer bearing ring. The bearing seat is connected with the rotor through a bearing, the outer culvert bearing ring is connected with the outer culvert casing, the inner side of the bearing frame is connected with the bearing seat, the outer side of the bearing frame is connected with the outer culvert bearing ring through a short pull rod, and the short pull rod plays a role in adjusting the concentricity of the inner culvert casing and the outer culvert casing.
The bearing frame is the bearing piece of the bearing casing assembly closest to the gas channel. The bearing frame is formed into a basic structure by connecting a plurality of radial force transmission support plates distributed in the circumferential direction with an inner casing and an outer casing, a gas flow channel is formed between the support plates, the bearing frame is simultaneously subjected to all mechanical loads transferred by thermal loads and fulcrums in the working state, and the special stress concentration of the support plate root switching area and other parts makes the bearing frame become one of typical weak structures of an aeroengine, so that the reliability and the service life of the bearing frame are often difficult to ensure.
Disclosure of Invention
The application aims to provide an aeroengine turbine bearing casing supporting structure, which solves or reduces at least one problem in the background art.
The technical scheme of the application is as follows: an aeroengine turbine power bearing case support structure comprising: an inner culvert load-carrying ring, an outer culvert load-carrying ring, a bidirectional load-carrying rod, a load-carrying rod mounting seat and a load-carrying rod tensioning screw;
The bidirectional bearing rod comprises a main body section, connecting sections positioned at two ends of the main body section and ball sockets positioned in the connecting sections, wherein joint ball heads are arranged in the ball sockets;
Be equipped with the bearing frame on the inner culvert load ring, be equipped with the mount pad on the outer culvert load ring, on the bearing frame of inner culvert load ring was installed through joint bulb and connecting piece to the one end of two-way load bar, the other end of two-way load bar is installed on the load bar connecting seat through joint bulb and connecting piece, and the load bar connecting seat inserts in the mount pad of outer culvert load ring to install on the mount pad through the load bar tensioning screw of radial setting.
Further, the two-way bearing rods are multiple, and the two-way bearing rods are uniformly distributed on the axis of the engine.
Further, the gas turbine engine further comprises a fairing, wherein the fairing is arranged on the outer side of the bidirectional bearing rod and used for separating the bidirectional bearing rod from the gas channel.
Furthermore, a gap is arranged between the connecting seat of the bearing rod and the bottom of the mounting seat, and the same or similar tightening torque is applied to the tensioning screws of the bearing rods at each position, so that each bidirectional bearing rod is in the same tightening state, and concentric control of the inner bearing ring and the outer bearing ring in the engine assembling state is realized through the bidirectional bearing rods.
Further, the support structure further comprises: and the gland is radially connected with the mounting seat of the outer culvert load-bearing ring by adopting a dovetail connection structure and is used for pressing the tension screw of the load-bearing rod on the mounting seat of the outer culvert load-bearing ring.
Further, the support structure further comprises: the gland compression screw is connected with the gland through radial threads, and the lower end of the gland compression screw is propped against the bearing rod to tighten the screw.
Furthermore, the gland is provided with a through groove with the width larger than the distance between the two sides of the head of the tension screw of the force-bearing rod, so that a gap is formed between the gland and the two parallel sides of the head of the tension screw of the force-bearing rod, and the tension screw of the force-bearing rod is prevented from rotating or loosening.
Furthermore, the central area of the head of the tension screw of the force-bearing rod is provided with a circular pit, the diameter of the circular pit is larger than that of the end head of the gland compression screw, and the gland compression screw is tightly pressed with the bottom surface of the circular pit when assembled, so that the functions of positioning the gland and preventing falling are achieved.
Further, the head of the gland compression screw and the gland are provided with wire locking holes, and the gland compression screw and the gland are locked by the wire locking holes so as to prevent the gland compression screw from loosening.
The bearing case supporting structure provided by the application realizes direct force transmission to the outer bearing ring through the bearing seat of the inner bearing ring, meets the functional requirements of the engine on the tensile and tensile bidirectional force transmission under different working states, improves the stress condition of the bearing frame, improves the reliability and service life of the bearing frame, and has important significance for the design of the aeroengine with high thrust-weight ratio and long service life.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
Fig. 1 is a schematic view of a supporting structure of a turbine bearing casing of an aeroengine.
FIG. 2 is a schematic view of a bi-directional load beam according to the present application.
Fig. 3 is a front view of an aero-engine turbine bearing case support structure of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to solve the problems of low reliability, short service life and the like of a bearing frame in the prior art, the application provides a supporting structure of a turbine bearing casing of an aeroengine, by arranging a tensile and compressive bidirectional bearing rod between an inner bearing ring and an outer bearing ring, the engine part of the maneuvering load is directly transmitted to the outer bearing ring through the bidirectional bearing rod, so that the maneuvering load can be shared by the bearing frame, the stress condition of the bearing frame is improved, and the reliability and the service life of the bearing frame are improved.
As shown in fig. 1 to 3, an aeroengine turbine bearing casing support structure 100 provided by the present application includes: an inner culvert load ring 110, an outer culvert load ring 120, a bi-directional load bar 130, a load bar mount 140, and load bar tension screws 150.
The bidirectional bearing rod 130 comprises a main body section 131, two connecting sections 132 and ball sockets 133 which are respectively positioned in the two connecting sections 132 and used for installing joint balls 134. The bidirectional bearing rod 130 is connected with other components through the joint ball heads 134 at the two ends, the matching structure of the ball socket 133 and the spherical surface of the joint ball heads 134 reserves the torsion freedom degree of the two ends of the bidirectional bearing rod, and the unsynchronized axial and circumferential deformation at the two ends of the bidirectional bearing rod can be effectively coordinated, so that additional bending moment is avoided.
The inner bearing ring 110 is provided with a radial bearing seat 111, and the lower end of the bidirectional bearing rod 130 is mounted on the bearing seat 111 of the inner bearing ring 110 through a joint ball 134 and a connecting piece. The outer culvert bearing ring 120 is also provided with a radial mounting seat 121, the upper end of the bidirectional bearing rod 130 is mounted on the bearing rod connecting seat 140 through the joint ball head 134 and a connecting piece, and the bearing rod connecting seat 140 is inserted into the mounting seat 121 and is mounted on the mounting seat 121 through a radially arranged bearing rod tensioning screw 150.
It should be noted that, in the turbine bearing casing supporting structure of the present application, a plurality of uniformly distributed bidirectional bearing rods 130 are adopted to jointly implement the bearing function. Further, in order to avoid exposing to the main stream of fuel gas to excessive heat load during the operation state of the bi-directional load bearing bars 130, the present application provides a fairing 180 on the outside of each bi-directional load bearing bar 130 to isolate it from the fuel gas channel.
As a connecting piece between the inner culvert and the outer culvert bearing ring of the turbine bearing casing, the bidirectional bearing rod 130 should play a role in adjusting the concentricity of the inner culvert casing and the outer culvert casing during the assembly of the engine. In the present invention, a certain gap is radially provided between the head of the force-bearing rod coupling seat 140 and the bottom of the hole of the mounting seat 121 on the outer culvert force-bearing ring 120, and when the engine is assembled, the same tightening torque is applied to each force-bearing rod tightening screw 150 to make each bidirectional force-bearing rod 130 in the same tightening state, and at this time, concentric control of the inner and outer culvert force-bearing rings is realized by the bidirectional force-bearing rods 130 in the assembled state.
In the high temperature operation state, the main body segment 131 of the bi-directional bearing bar 130 is separated from the fuel gas by the fairing 180, but still is influenced by strong heat radiation, so that the temperature level is far higher than that of the bearing blocks 111 of the outer bearing ring 120 and the inner bearing ring 110, and even if the material with the expansion coefficient significantly lower than that of the outer bearing ring 120 is used, the radial thermal expansion amount of the material is inevitably higher than that of the outer bearing ring 130. Therefore, in the present application, in the high temperature operation state, the pressure between the contact surface of the tension screw 150 of the load-bearing bar and the mounting seat 121 of the outer culvert load-bearing ring 120 is eliminated, and the bi-directional load-bearing bar 130 is released from the tension state. Because of the existence of radial gaps between the head of the bearing rod connecting seat 140 and the bottom of the hole of the mounting seat 121 of the outer bearing ring 120, if other mounting structures are not provided, part or all of the bidirectional bearing rods are separated from contact with the outer bearing ring 130, and the expected force transmission function is lost. In order to ensure that the bearing structure of the bi-directional bearing bar 130 is in close contact with the outer bearing ring 120 in the heated state, the support structure 100 of the present application further includes a pressing cover 160 for pressing the bearing bar tension screw 150 against the mounting seat 121 of the outer bearing ring 120. The gland 160 is radially connected with the outer culvert load-bearing ring 120 through a dovetail connection structure, so that stress concentration at each junction of the gland 160 and the mounting seat 121 of the outer culvert load-bearing ring 120 is limited to the greatest extent, and the stress level is effectively controlled.
Because of the machining tolerances of the parts, the tight connection between the bi-directional load-bearing bar load-bearing structure and the outer culvert load-bearing ring 120 cannot be ensured only by the gland 160, and the existence of the radial gap between the two can affect the function of the bi-directional load-bearing bar load-bearing structure. Therefore, the support structure of the present application further includes a gland compression screw 170, the gland compression screw 170 is connected with the gland 160 through radial threads, the lower end of the gland compression screw is pressed against the tension screw 150 of the load-bearing rod, at this time, the tension screw 150 of the load-bearing rod is tightly connected with the mounting seat 121 of the outer load-bearing ring 120 in two directions through the gland 160 and the gland compression screw 170, the load-bearing structure of the two-way load-bearing rod is not separated from the outer load-bearing ring in a high-temperature heated state, but is in a pressed state, and the two-way load-bearing rod 130 plays a role of transferring force in a tensioned and pressed two-way load-bearing state.
The assembling process of the supporting structure of the bearing casing component is as follows:
Firstly, a ball socket 133 at one end of a bidirectional bearing rod 130 is internally provided with a joint ball 134, then the ball socket is connected with a bearing seat 111 of an inner bearing ring 110 through a connecting piece, a bearing rod connecting seat 140 is sleeved into an installation seat 121 of an outer bearing ring 120 at the other end of the bidirectional bearing rod 130, then the ball socket 133 of the bidirectional bearing rod 130 is also internally provided with the joint ball 134, and then the ball socket is pushed into the bearing rod connecting seat 140 to connect the ball socket and the bearing rod through the connecting piece;
in the state of keeping the inner and outer culvert load rings concentric, the same or similar tightening torque is applied to each load rod tightening screw 150, so that each bidirectional load rod 130 is in the same or similar tightening state, and the concentricity of the inner and outer culvert load rings is ensured.
In the present application, the head of the tension screw 150 has a hexagonal structure, any two parallel sides of the hexagon are parallel to two wedge-shaped sides (i.e. the pushing direction of the gland 160) in the circumferential direction of the mounting seat 121 during assembly, then the gland 160 is pushed in along the wedge-shaped sides, and the gland 160 and the tension screw 150 are radially compressed by the gland compression screw 170.
The gland 160 is provided with a through groove with a width slightly larger than the distance between the two side surfaces of the head of the tension screw 150 of the force-bearing rod, and a certain small gap is reserved between the two parallel side edges of the head of the tension screw 150 of the force-bearing rod, so as to play a role in preventing the tension screw 150 of the force-bearing rod from rotating or loosening; the central area of the head of the tension screw 150 of the bearing rod is provided with a circular pit with a certain depth, the diameter of the pit is slightly larger than that of the gland compression screw 170, and the gland compression screw 170 is compressed with the bottom surface of the pit when assembled, so that the functions of positioning the gland 160 and preventing falling are achieved; the head of the gland compression screw 170 and the gland 160 are provided with locking screw holes, and the head and the gland are locked by locking screws so as to prevent the gland compression screw 170 from loosening.
The bearing casing supporting structure provided by the application realizes direct force transmission to the outer bearing ring through the bearing seat, meets the functional requirements of the engine on the bearing and bearing bidirectional force transmission under different working states, improves the stress condition of the bearing frame 200, improves the reliability and service life of the bearing frame, and has important significance for the design of the aeroengine with high thrust-weight ratio and long service life.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411033437.5A CN118815555B (en) | 2024-07-30 | 2024-07-30 | A turbine bearing casing support structure for an aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411033437.5A CN118815555B (en) | 2024-07-30 | 2024-07-30 | A turbine bearing casing support structure for an aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN118815555A true CN118815555A (en) | 2024-10-22 |
| CN118815555B CN118815555B (en) | 2026-01-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411033437.5A Active CN118815555B (en) | 2024-07-30 | 2024-07-30 | A turbine bearing casing support structure for an aero-engine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB807801A (en) * | 1956-03-09 | 1959-01-21 | Federated Foundries Ltd | Improvements in or relating to gland joints for plumbing systems |
| CN201272399Y (en) * | 2008-08-22 | 2009-07-15 | 重庆建设摩托车股份有限公司 | Front wheel constraining and adjusting device of four-wheeled vehicle travelling on sandbeach |
| CN206216596U (en) * | 2016-11-21 | 2017-06-06 | 四川达宇特种车辆制造厂 | A kind of turbojet engine housing assembly tooling |
| CN117145594A (en) * | 2023-11-01 | 2023-12-01 | 中国航发沈阳发动机研究所 | Force transmission structure of inner and outer casing of turbine |
| WO2024017261A1 (en) * | 2022-07-18 | 2024-01-25 | 中国航发商用航空发动机有限责任公司 | Turbine guide vane and turbine containing same, and aeroengine |
-
2024
- 2024-07-30 CN CN202411033437.5A patent/CN118815555B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB807801A (en) * | 1956-03-09 | 1959-01-21 | Federated Foundries Ltd | Improvements in or relating to gland joints for plumbing systems |
| CN201272399Y (en) * | 2008-08-22 | 2009-07-15 | 重庆建设摩托车股份有限公司 | Front wheel constraining and adjusting device of four-wheeled vehicle travelling on sandbeach |
| CN206216596U (en) * | 2016-11-21 | 2017-06-06 | 四川达宇特种车辆制造厂 | A kind of turbojet engine housing assembly tooling |
| WO2024017261A1 (en) * | 2022-07-18 | 2024-01-25 | 中国航发商用航空发动机有限责任公司 | Turbine guide vane and turbine containing same, and aeroengine |
| CN117145594A (en) * | 2023-11-01 | 2023-12-01 | 中国航发沈阳发动机研究所 | Force transmission structure of inner and outer casing of turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN118815555B (en) | 2026-01-09 |
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