JP2002242699A - Gas turbine engine with foreign matter removal structure - Google Patents

Abstract

(57) [Problem] To provide a gas turbine engine provided with a foreign matter removing structure that can be provided inexpensively and compactly by using existing parts for the engine. SOLUTION: At a radially outer peripheral portion of a curved passage 14 connected downstream of a centrifugal compressor 1, a collecting port 17 is formed to allow foreign matter E in air A to enter and to be drawn out of the curved passage 14. A collection port 39 is formed at the boundary between the top wall 37 and the peripheral wall 38 in the outer cylinder 11 of the combustion chamber C of the combustor 4. A collection port 61 is formed in the compressor shroud 51 of the axial compressor 44.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine engine mainly used as a power source of an aircraft such as a helicopter, a driving source of a generator, and the like. And a device provided with a foreign matter removing structure that can be collected and removed.

[0002]

2. Description of the Related Art In a gas turbine engine used for the above-mentioned applications, foreign matters such as sand, pebbles, metal pieces or twigs are liable to enter the engine while being contained in intake air, and these foreign matters are likely to enter the engine. If the vehicle collides with the compression blades or turbine blades of the engine, the engine may be damaged by damage caused by the impact received at the time of the collision. In particular, engines with ceramic turbine blades that are brittle against impact
Even fine foreign matter, which has not been a problem in the past, can be damaged and cause a failure. That is, in an engine having ceramic turbine blades, not only foreign substances contained in intake air but also foreign substances such as cutting powder and carbon lumps generated inside cause damage.

[0003] Therefore, conventionally, after the sucked air is swirled or passed through a curved passage, foreign matter heavier than air is removed from the air flow path by centrifugal force by being introduced into the engine. IPS (inlet particle) that draws out in the direction and removes it, and inhales only air into the engine
separator) is widely used.

[0004]

However, it is difficult for the conventional foreign matter removing means (IPS) to prevent light foreign matter from entering the inside of the engine. Cannot be removed. Further, with conventional means such as IPS, the collected foreign matter cannot be taken out until the engine is disassembled at the time of periodic inspection or the like.

In view of the above, the present invention has been made in view of the above-mentioned conventional problems, and a foreign matter removing structure can be provided in a compact and inexpensive manner by using existing parts in an engine. It is an object of the present invention to provide a gas turbine engine that can arbitrarily take out the gas turbine engine.

[0006]

In order to achieve the above object, a gas turbine engine according to a first configuration of the present invention comprises:
Downstream of the diffuser of the centrifugal compressor in the gas turbine engine, a curved passage is formed to change the air from the diffuser from radially outward to axially rearward or radially inward. A collection port is formed at a radially outer peripheral portion to allow foreign matter in the air to enter and to be drawn out of the curved air path.

According to this structure, the air discharged from the diffuser flows with a swirl component, and foreign matter contained in the air includes the centrifugal force due to the swirl of the air and the bending of the curved passage. And the inertial force that tends to flow against the surface. Therefore, while the air is forced to flow along the curved passage, the foreign matter heavier than the air is separated from the curved passage and enters the collection port because a large centrifugal force and an inertial force are applied. Removed from the air. In general, the curved passage downstream of the centrifugal compressor has a relatively large bending angle, so that the effect of capturing foreign matter by the inertial force acting on the foreign matter is extremely large, and even a small foreign matter is almost certainly collected. Can be. Further, this foreign matter removing structure is different from a conventional foreign matter removing means in which a flow path is particularly greatly bent for removing foreign matter and is formed by using an existing curved passage at a radially outer peripheral portion of the curved passage. Since it is only necessary to provide a collecting port, the apparatus can be made compact and does not cause an increase in cost.

In a gas turbine engine according to a second aspect of the present invention, the combustor of the gas turbine engine has an inner cylinder forming a combustion chamber, an outer cylinder covering an outer peripheral portion and a top of the inner cylinder, and the inner cylinder And an introduction passage formed between the outer cylinder and introducing air from the compressor in a direction opposite to a flow direction of the combustion gas in the inner cylinder, and a top wall and a peripheral wall in the outer cylinder. Is formed at a boundary portion of the collection passage for allowing foreign substances in the air to enter and to be guided out of the introduction passage.

According to this configuration, since the compressed air flowing through the introduction passage has a swirl component, foreign matters contained in the compressed air are subjected to centrifugal force due to the swirl and the external cylinder. The inertial force generated by being turned at right angles by the top wall acts. Therefore, the foreign matter is separated from the compressed air, enters the collection port, and is collected. In addition, this foreign matter removing structure uses an existing introduction passage without particularly bending the flow path of the compressed air, and only provides a collection port at the boundary portion outside the end of the introduction passage. Since it is good, it can be configured compactly and does not cause an increase in cost.

Further, in the gas turbine engine according to the third configuration of the present invention, the foreign matter in the air enters the compressor shroud forming the outer peripheral wall of the air passage of the axial flow compressor in the gas turbine engine. A collection port leading out of the passage is formed.

According to this structure, since the air flowing through the air passage of the axial compressor is swirling, the centrifugal force due to the swirl acts on the foreign matter contained in the air, and the foreign matter is more than the air. Since it is heavy, it receives a relatively large centrifugal force, so that it is removed from the air passage and enters the collection port to be collected. Also in this foreign matter removing structure, it is only necessary to provide a collecting port in a part of the existing compressor shroud without specially bending the air passage, so that the structure can be made compact and increase the cost. Absent.

In the first to third configurations, the collecting port is preferably formed in an annular shape concentric with the axis of the engine, so that foreign substances can be collected on the entire circumference of the air passage.

[0013] In the first to third configurations, it is preferable that an outlet for taking out the collected foreign matter to the outside of the engine, and a plug for opening and closing the outlet are provided. Thus, the collected foreign matter can be discharged to the outside simply by opening the outlet with the plug without disassembling the engine.

[0014]

Preferred embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 is a longitudinal sectional view showing a schematic configuration of a gas turbine engine provided with a foreign matter removing structure according to a first embodiment of the present invention.

This gas turbine engine is a two-stage centrifugal compressor 1 that draws air A from an air inlet IN and compresses it.
And a combustor 4 for supplying fuel to the compressed air A for combustion, and a turbine 7 driven by combustion gas G. The compressor 1 and the turbine 7 include a housing 13
The combustor 4 is mounted on the housing 13 so as to protrude. The combustion gas G generated in the combustion chamber C of the combustor 4 is guided to the turbine 7 via the scroll 9 to rotate the turbine 7, and the two-stage centrifugal compressor connected to the turbine 7 by the rotating shaft 10. 1 and a rotating load L such as a generator or a helicopter rotor.

The combustor 4 is of a single-can type (or a multi-can type), and is provided so as to protrude substantially in the radial direction of the turbine 7. The combustor 4 includes an inner cylinder 8 forming a combustion chamber C,
Outer cylinder 11 covering outer peripheral portion 8a and top 8b of inner cylinder 8
And an introduction passage 12 is formed between the inner cylinder 8 and the outer cylinder 11 to introduce the compressed air CA from the compressor 1 in a direction opposite to the flow direction of the combustion gas G in the inner cylinder 8. I have. Compressor 1
The compressed air CA supplied from the inside flows into the introduction passage 12 toward the tip side of the combustor 4, is deflected toward the center side of the combustor 4, enters the inner cylinder 8, and After being mixed with the fuel supplied from the fuel nozzle 13 and burned to become a combustion gas G, it flows toward the base end side of the combustor 4.
The two compression stages 2 and 3 constituting the centrifugal compressor 1 are fixed to the housing 13 on the downstream side of the rotating impeller rotors 2a and 3a to suppress the turning of the air A and convert the dynamic pressure to the static pressure. Diffusers 2b and 3b for increasing the static pressure.

The diffuser is provided between the discharge port 2ex of the first compression stage 2, ie, the downstream end of the diffuser 2b, and the suction port 3in of the second compression stage 3, ie, the suction end of the impeller rotor 3a. A curved passage 14 is formed to turn the air A from 2b so as to make a U-turn from radially outward to radially inward of the gas turbine engine.

As shown in FIG. 2 which is an enlarged view of a portion II in FIG. 1, a foreign matter E in the air A enters the engine housing 13 which forms the radially outer peripheral portion of the curved passage 14 so as to be bent. The collection port 17 led out of the rotary shaft 10
(FIG. 1), that is, the axis 2 of the gas turbine engine
5, a collection chamber 18 for foreign matter E is provided at the back of the collection port 17. further,
An outlet 19 formed of a screw hole communicating with the outside is formed in the collection chamber 18, and a plug 20 made of a bolt is detachably screwed into the outlet 19. A plurality of outlets 19 that are opened and closed by the attachment and detachment of the plug 20 may be formed in the circumferential direction, or may be provided at a lower portion of the annular collection chamber 18 as shown in FIG.

Generally, the air A discharged from the diffuser 2b flows with a swirling component. Therefore, if the air A contains foreign matter E, the foreign matter E Centrifugal force due to the turning and inertial force due to the bending along the curved passage 14 act. Therefore, the foreign matter E, which is heavier than the air A, is displaced radially outward from the curved passage 14, enters the collection port 17 in FIG. 2, and is stored in the collection chamber 18.

In the above foreign matter removing structure, since the bending angle of the curved passage 14 is as large as about 180 °, the effect of collecting the foreign matter E by the inertial force is extremely large, and the small foreign matter E
Even in this case, it is possible to collect in the collection chamber 18 almost certainly. Further, this foreign matter removing structure is different from the conventional foreign matter removing means in which the flow path is particularly greatly bent, and has a collection port 17 at a radially outer peripheral portion of the curved passage 14 by utilizing the existing curved passage 14. Since only the collection chamber 18 needs to be provided, the apparatus can be made compact and the cost does not increase.

Further, when the engine is stopped, the foreign matter E stored in the collection chamber 18 is removed from the lower plug 20 shown in FIG.
When the engine is driven, the upper plug 20 can be removed and the air can be blown off toward the outlet 19 by air pressure to remove the oil. can do. In addition, if the opening 19 can be automatically opened and closed by an electromagnetic valve or the like instead of the plug 20, the foreign matter can be easily opened and foreign substances can be discharged even during operation of the engine.

FIG. 3 is an enlarged view of part III of FIG.
At the discharge port 3ex of the third compression stage 3, the diffuser 3
A curved passage 21 is formed for turning the air A from b outwardly in the radial direction of the gas turbine engine from rearward in the axial direction of the engine (rightward in the figure).

In the engine housing 13 which forms the radially outer peripheral portion of the curved passage 21, a collection port 22 through which the foreign matter E in the air A enters and is drawn out of the curved passage 21 is provided on the rotating shaft 10 (FIG. 1). ) Is formed in an annular shape concentric with the axis 25, and a collection chamber 23 for the foreign matter E is provided at the back of the collection port 22. Further, an outlet 24 formed of a screw hole communicating with the outside is formed in the collection chamber 23, and a plug 27 made of a bolt is detachably screwed into the outlet 24. A plurality of outlets 24 that are opened and closed by the attachment and detachment of the plug 27 may be formed in the circumferential direction.
As shown in the figure, only one may be provided in the lower part of the annular collection chamber 23.

In this foreign matter removing structure, substantially the same effect as the structure shown in FIG. 2 can be obtained. That is, the foreign matter E contained in the air A receives the centrifugal force due to the swirling of the air A and the inertial force due to the bending along the curved passage 21, and is removed radially outward from the curved passage 21 and collected. It enters the mouth 22 and is stored in the collection chamber 23. Also in this foreign matter removing structure, the bending angle of the curved passage 21 is substantially 90 °.
Therefore, the effect of collecting the foreign matter E by the inertial force is large, and even the small foreign matter E can be almost certainly collected in the collection chamber 23.

FIG. 4 shows a foreign matter removing structure according to a modification of the first embodiment of the present invention. This foreign matter removing structure is applied to a gas turbine engine provided with the two-stage centrifugal compressor 1 shown in FIG. 1, and instead of the collecting chamber 18 in FIG.
The existing closed space formed between the compression stages 2 and 3 is used as the collection chamber 28. The collection chamber 28 is an annular space concentric with the axis 25 (FIG. 1) of the engine. A trapping port 29 for allowing the foreign matter E in the air A to enter and exit outside the curved passage 14 at the radially outer peripheral portion of the curved passage 14.
And a collection passage 30 communicating with the collection chamber 28 is formed in an annular shape concentric with the axis 25 (FIG. 1) of the rotating shaft 10. An outlet 31 formed of a screw hole communicating with the outside is formed between the collection passage 30 and the collection chamber 28,
A plug 32 made of a bolt is detachably screwed into the outlet 31. A plurality of outlets 31 may be formed in the circumferential direction, or only one outlet 31 may be provided in the lower part of the annular collection chamber 28.

Since this foreign matter removing structure has substantially the same configuration as that of FIG. 2, it operates in the same manner as described with reference to the structure of FIG. That is, the foreign matter E contained in the air A is
Receiving the centrifugal force due to the turning of the air A and the inertia force due to the bending of the curved passage 14, the air A is displaced radially outward from the curved passage 14 and enters the collection port 29, and then is captured through the collection passage 30. It is stored in the collection room 28.

In addition, the foreign matter removing structure uses the existing curved passage 14 and a sealed space between the two compression stages 2 and 3 of the centrifugal compressor 1 to collect the foreign matter on the radially outer peripheral portion of the curved passage 14. Since only the opening 29 and the collecting passage 30 need to be provided, the structure can be made compact and the cost does not increase. The foreign matter E stored in the collection chamber 28 is
If the lower plug (not shown) is removed when the engine is stopped, or any of the plugs 32 is removed while the engine is running, the air can be discharged from the outlet 31 to the outside by air pressure. In addition, since the foreign matter removing structure includes the collecting chamber 28 having a large volume, there is an advantage that the frequency of discharging the foreign matter E during storage can be reduced.

FIG. 5 is a longitudinal sectional view showing a configuration of a main part of a gas turbine engine having a foreign matter removing structure according to a second embodiment of the present invention. This foreign matter removing structure is provided in the combustor 4 of the gas turbine engine shown in FIG.
The same or equivalent components as those in FIG. 1 are denoted by the same reference numerals. A swirler 34 is attached to the top 8b of the inner cylinder 8 of the combustor 4 of FIG. 1 so as to surround the fuel nozzle 13, and the compressed air CA from the centrifugal compressor 1
2 through the combustion or dilution air holes 33 of the inner cylinder 8 into the combustion chamber C, and the other part into the introduction passage 1.
It makes a U-turn from 2 and flows into the combustion chamber C while turning by passing through the swirler 34.

The foreign matter removing structure of this embodiment has the outer cylinder 11
At the boundary between the top wall 37 and the peripheral wall 38, there is formed a collecting port 39 for allowing the foreign matter E contained in the compressed air CA to enter and exit the introduction passage 12, and a peripheral wall corresponding to the back of the collecting port 39. 38 is provided with a collection chamber 40. Further, an outlet 41 formed of a screw hole communicating with the lower outside is formed in the collection chamber 40, and a plug 42 made of a bolt is detachably screwed into the outlet 41.

Generally, the compressed air CA flowing through the introduction passage 12 has a swirl component added by the compressor 1, so that if the compressed air CA contains foreign matter E, the foreign matter E A centrifugal force due to the turning and an inertial force generated by being changed to a right angle by the top wall 37 of the outer cylinder 11 act on E. Therefore, the foreign matter E, which is heavier than the compressed air CA, separates from the compressed air CA, enters the collection port 39, and is stored in the collection chamber 40.

In the above foreign matter removing structure, since both the inertial force and the turning force acting on the foreign matter E are large, the small foreign matter E
Even with this, the liquid can be almost certainly led out of the collection port 39 to the outside of the introduction passage 12 and collected in the collection chamber 40. Also,
This foreign matter removing structure is different from the conventional foreign matter removing means in which the flow path is particularly largely bent, by using the existing introduction passage 12 and collecting the collecting port at the boundary portion outside the end of the introduction passage 12. Since it is only necessary to provide the collection chamber 40 having 39, the apparatus can be made compact and cost increase does not occur.

The foreign matter E stored in the collection chamber 40 is
If the plug 42 is removed at the time of stopping or driving the engine, it can be discharged from the outlet 41 to the outside. When the engine is stopped, the top wall 37 is removed to remove the foreign matter E.
Is also easy to remove. In this foreign matter removing structure, as shown by a two-dot chain line, if a concave guide recess 43 having a curved cross section is formed on the lower surface of the top wall 37 in the radial direction inside the collection port 39, compressed air CA is formed. The foreign matter E inside can be smoothly guided into the collection port 39.

FIG. 6 is a partially cutaway side view showing a schematic configuration of a gas turbine engine having a foreign matter removing structure according to a third embodiment of the present invention. First, the configuration of the gas turbine engine will be briefly described.

This gas turbine engine compresses air A by an axial compressor 44 and guides the air A to a combustor 47, and injects gas fuel or liquid fuel into the combustor 47 to burn it, and burns it at high temperature and high pressure. The turbine 48 is driven by the gas G. The axial compressor 44 includes a rotating shaft 4.
9 and a plurality of stationary blades 52 arranged in a plurality of stages on an inner peripheral surface of a compressor shroud 51 forming an outer peripheral wall of an air passage 67 of the axial flow compressor 44.
The air A sucked from the intake duct 53 is compressed by the combination of the above and the compressed air CA is supplied to the annularly formed cabin 54.

A plurality (for example, six) of the combustors 47 are arranged in the annular casing 54 at equal intervals along the circumferential direction thereof, and the compressed air CA supplied to the casing 54 is As shown by the arrows a and b, through the substantially cylindrical outer cylinder 56,
It is led to a combustion chamber 58 in a substantially cylindrical inner cylinder 57. On the other hand, in the combustor 47, fuel F is injected from a fuel nozzle 59 into the combustion chamber 58, and the fuel F is mixed with the compressed air CA and burned, and the high-temperature and high-pressure combustion gas G flows downstream of the inner cylinder 57. Through the transfer duct 60 connected to the side of the turbine 4
8

FIG. 7 is an enlarged view of a portion VII in FIG.
3 shows a foreign matter removing structure of the gas turbine engine. This foreign matter removing structure is a collection port that allows foreign matter E in the air A to enter the compressor shroud 51 and exit to the outside of the air passage 67 near the rear end of the rotor blade 50 in the last stage in the axial flow compressor 44. 61 is formed in an annular shape concentric with the axis of the rotating shaft 49, that is, the axis 25 (FIG. 6) of the gas turbine engine, and a collection chamber 62 for the foreign matter E is provided at the back of the collection port 61. Have been. Further, an outlet 63 formed of a screw hole communicating with the outside is formed in the collection chamber 62, and a plug 64 made of a bolt is detachably screwed into the outlet 63. A plurality of outlets 63 that are opened and closed by the attachment and detachment of the plug 64 may be formed in the circumferential direction, or only one outlet 63 may be provided in the lower part of the annular collection chamber 62 as shown in FIG.

In the axial compressor 44, the air A is swirled by the moving blades 50. If the foreign matter E is contained in the air A, a centrifugal force due to the swirl acts on the foreign matter E. . Therefore, the air A flows along the air passage 67, but the foreign matter E, which is heavier than the air A, is radially outwardly collected from the air passage 67 because a relatively large centrifugal force acts thereon. It enters the mouth 61 and is stored in the collection chamber 62.

Further, this foreign matter removing structure has a collecting chamber 62 having a collecting port 61 in a part of the existing compressor shroud 51.
, It is possible to make the device compact and to avoid cost increase.

Further, when the engine is stopped, the foreign matter E stored in the collection chamber 62 is removed from the lower plug 6 shown in FIG.
If the plug 4 is removed, it can be naturally dropped from the outlet 63 and discharged. In addition, if any plug 54 is removed while the engine is running, the plug is blown off toward the outlet 63 by air pressure and discharged to the outside. You can also.

[0040]

As described above, according to the gas turbine engine of the present invention, the existing curved passage connected downstream of the diffuser of the centrifugal compressor, the existing outer cylinder of the combustor, or the existing external cylinder or axial flow compressor can be used. The existing compressor shroud is provided with a collection port that allows foreign substances contained in the air that are heavier than the air to enter using the turning force and the inertia force. The compact foreign matter removing structure used can be configured at low cost.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view showing a schematic configuration of a gas turbine engine provided with a foreign matter removing structure according to a first embodiment of the present invention.

FIG. 2 is an enlarged view of a portion II in FIG.

FIG. 3 is an enlarged view of a part III in FIG. 1;

FIG. 4 is a longitudinal sectional view showing a configuration of a main part of a gas turbine engine provided with a foreign matter removing structure according to a modification of the embodiment.

FIG. 5 is a longitudinal sectional view showing a main configuration of a gas turbine engine provided with a foreign matter removing structure according to a second embodiment of the present invention.

FIG. 6 is a partially broken side view showing a schematic configuration of a gas turbine engine provided with a foreign matter removing structure according to a third embodiment of the present invention.

FIG. 7 is an enlarged view of a section VII in FIG. 6;

[Explanation of symbols]

1: Centrifugal compressor, 2b, 3b: Diffuser, 4, 4
7, 58: combustor, 8: inner cylinder, 11: outer cylinder, 12: introduction passage, 14, 21: curved passage, 17, 22, 29, 3,
9, 61 ... collecting port, 19, 24, 41, 63 ... outlet,
20, 27, 42, 64 ... plug, 25 ... shaft center, 37 ...
Top wall, 38: peripheral wall, 44: axial compressor, 51: compressor shroud, 58: combustion chamber, 67: air passage, A: air,
E: foreign matter, C: combustion chamber.

Claims (5)

[Claims] 1. A curved passage is formed downstream of a diffuser of a centrifugal compressor in a gas turbine engine to redirect air from the diffuser from radially outward to axially rearward or radially inward. A gas turbine engine in which a collecting port is formed at a radially outer peripheral portion of the curved passage so as to allow foreign matter in the air to enter and exit the curved air passage. 2. A gas turbine engine comprising a combustor having an inner cylinder forming a combustion chamber, an outer cylinder covering an outer peripheral portion and a top of the inner cylinder, and a compression formed between the inner cylinder and the outer cylinder. An introduction passage for introducing air from the machine in a direction opposite to the flow direction of the combustion gas in the inner cylinder, and foreign matter in the air enters a boundary between the top wall and the peripheral wall in the outer cylinder. A gas turbine engine having a trapping port formed outside the introduction passage. 3. A compressor shroud forming an outer peripheral wall of an air passage of an axial compressor in a gas turbine engine,
A gas turbine engine having a collection port for allowing a foreign substance in the air to enter and exit outside the air passage. 4. The gas turbine engine according to claim 1, wherein the collection port is formed in an annular shape concentric with the axis of the engine. 5. The gas turbine engine according to claim 1, further comprising an outlet for taking out the trapped foreign matter outside the engine, and a plug for opening and closing the outlet.