JP2003269191A - Gas turbine engine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To stably extract motive power from a high pressure turbine shaft 15. <P>SOLUTION: When applying rotational torque in one direction to a housing 57 in a state of inserting a tip part of the housing 57 into an inserting hole 61, a pressing surface 81F of a fitting projection part 81 for the housing presses a pressing object surface 79F of a fitting recessed part 79 for a hole, and the center of the housing 57 is matched with the center of the inserting hole 61 so that a motive power extracting shaft 65 is aligned. <P>COPYRIGHT: (C)2003,JPO

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 such as a jet engine having a function of extracting power from rotation of a turbine shaft.

[0002]

2. Description of the Related Art It is widely known that power is extracted from rotation of a turbine shaft in a gas turbine engine such as a jet engine. In order to extract power from the rotational force of the turbine shaft, the gas turbine engine It has such a configuration.

That is, a base end portion of a cylindrical housing is attached to an edge portion of an attachment hole formed in an engine case of a gas turbine engine, and a tip end portion of the housing is attached to the engine case. It can be inserted into an insertion hole formed on the turbine shaft side of the hole. A power extraction shaft is rotatably provided in the housing, and a tip portion of the power extraction shaft projects toward the turbine shaft side with respect to the housing. Here, the distal end portion of the housing is configured to be connected to the turbine shaft when inserted into the insertion hole, and the base end portion of the power extraction shaft is connected to an appropriate drive device such as a lubricating oil supply pump. It is connected.

Therefore, the front end of the housing is inserted into the insertion hole to connect the power extraction shaft to the turbine shaft, and the base end of the housing is attached to the engine case. This completes the preparation for obtaining power from the rotation of the turbine shaft by the power extraction shaft.

After the preparation is completed, the high temperature and high pressure combustion gas is expanded to rotate the turbine shaft. Thus, the power extraction shaft can be rotated in conjunction with the turbine shaft, in other words, the power can be obtained from the rotation of the turbine shaft to obtain a force, and the power can be transmitted to the drive device.

[0006]

By the way, in order to insert the front end of the housing into the insertion hole, a certain amount of space is provided between the outer peripheral surface of the front end of the housing and the inner peripheral surface of the insertion hole. While necessary, this gap reduces the support rigidity of the housing. Therefore, the rotation of the power extraction shaft causes the housing to resonate, which makes it difficult to stably extract power from the turbine shaft. Particularly, when the outer peripheral surface of the front end portion of the housing and the inner peripheral surface of the insertion hole are worn due to resonance of the housing, the support rigidity is further lowered, and the problem becomes more remarkable.

[0007]

According to a first aspect of the present invention, in a gas turbine engine that rotates a turbine shaft in an engine case by expanding a high temperature and high pressure combustion gas, a base end portion is A cylindrical housing that is attached to an edge of a mounting hole formed in the engine case and has a tip end that can be inserted into an insertion hole formed on the turbine shaft side of the mounting hole in the engine case, and is rotated in the housing. A power extraction shaft configured to be connectable to the turbine shaft when the distal end portion of the housing is inserted into the insertion hole, the power extraction shaft having a distal end protruding toward the turbine shaft side with respect to the housing; The hole fitting concave portion or the hole fitting convex portion formed on the inner peripheral surface of the insertion hole, and the hole fitting concave portion formed on the outer peripheral surface of the distal end portion of the housing. A housing fitting convex portion that fits into the housing fitting portion or a housing fitting concave portion that fits into the hole fitting convex portion, and the housing under a state in which a tip portion of the housing is inserted into the insertion hole. When a rotational torque is applied in one direction, the pressing surface of the housing fitting convex portion or the housing fitting concave portion is pressed by the hole fitting concave portion or the hole fitting convex portion. It is characterized in that it is configured to press the pressing surface.

According to the invention specifying matter of claim 1,
The tip of the housing is inserted into the insertion hole to connect the power extraction shaft to the turbine shaft. Furthermore, by applying a rotating torque in one direction to the housing under a state where the tip portion of the housing is inserted into the insertion hole,
The pressing surface of the housing fitting projection or the pressing surface of the housing fitting recess presses the pressed surface of the hole fitting recess or the pressed surface of the hole fitting projection. As a result, the tip of the housing is pressed in one direction on the inner peripheral surface of the insertion hole, and the support rigidity of the housing can be increased. Then, the base end portion of the housing is attached to the edge portion of the attachment hole of the engine case. Thus, the preparation for obtaining power from the rotation of the turbine shaft by the power extraction shaft is completed.

After the preparation is completed, the high temperature and high pressure combustion gas is expanded to rotate the turbine shaft. Thereby, the power extraction shaft can be rotated in conjunction with the turbine shaft, in other words, the power can be obtained from the rotation of the turbine shaft by the power extraction shaft.

According to the invention specifying matter of claim 2, in addition to the invention specifying matter of claim 1, a plurality of the hole fitting concave portions or the hole fitting convex portions (desirably, 3) are provided. One or more), and a plurality (preferably three or more) of the housing fitting projections or the housing fitting recesses,
When a rotational torque is applied to the housing in one direction under the condition that the tip portion of the housing is inserted into the insertion hole,
The pressing surface of the housing fitting convex portion or the pressing surface of the housing fitting concave portion presses the pressed surface of the hole fitting concave portion or the pressed surface of the hole fitting convex portion, and It is characterized in that the center of the housing coincides with the center of the insertion hole and the power extraction shaft is aligned.

According to the invention specifying matter of claim 2,
In addition to the operation according to the features of the invention as set forth in claim 1, by applying a rotational torque to the housing in one direction under a state in which the distal end portion of the housing is inserted into the insertion hole, the fitting protrusion for the housing is provided. The pressing surface of the portion or the pressing surface of the housing fitting concave portion presses the pressed surface of the hole fitting concave portion or the pressed surface of the hole fitting convex portion,
The power extraction shaft is aligned such that the center of the housing coincides with the center of the insertion hole.

According to the invention of claim 3, in addition to the matters specifying the invention of claim 1 or 2, there is provided a torque applying means for applying a rotational torque to the housing in one direction. It is characterized by

According to the invention specifying matter of claim 3,
In addition to the action according to the invention specifying matter of claim 1 or claim 2, the torque imparting means imparts a rotational torque to the housing in one direction under a state where the distal end portion of the housing is inserted into the insertion hole. Accordingly, the pressing surface of the housing fitting convex portion or the pressing surface of the housing fitting concave portion presses the pressed surface of the hole fitting concave portion or the pressed surface of the hole fitting convex portion.

[0014]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 is an enlarged view of a portion I in FIG. 3, and FIG. 2 is a sectional view of a jet engine according to an embodiment of the present invention. FIG. FIG. 4 is an enlarged view of the visual part II, and FIG.
FIG. 5 is an enlarged view along the line, and FIG. 5 shows IV-I in FIG. 1.
FIG. 6 is an enlarged view taken along the line V, and FIG. 6 is a view showing another mode in which the rotational torque is applied to the housing. here,
“Front” refers to the left side in FIGS. 1 to 6,
“Rear” means the right side in FIGS. 1 to 6.

As shown in FIG. 2, a jet engine (one of gas turbine engines) 1 according to the embodiment of the present invention is used in an aircraft, and includes a first engine case 3 and a first engine case 3. A hollow second engine case 5 integrally provided inside the engine case 3 is provided as a base. An annular engine flow passage 7 is formed inside the second engine case 5, and an annular bypass flow passage 9 is formed inside the first engine case 3 and outside the second engine case 5.

A low-pressure turbine shaft 11 is rotatably provided in the second engine case 5 via a plurality of bearings 13, and a hollow high-pressure turbine shaft 15 is provided in the second engine case 5 via a plurality of bearings 17. And is rotatable coaxially with the low-pressure turbine 11.

At the front end of the low-pressure turbine shaft 11, a fan 1 for taking air into the engine passage 7 and the bypass passage 9 is provided.
9 is provided, and the fan 19 is provided with an inlet cone 21 that guides air taken into the engine flow path 7 and the bypass flow path 9.

A low pressure compressor 2 is provided upstream of the engine flow path 7.
3 is provided, and the low-pressure compressor 23 sends the air to the downstream side (downstream in the gas flow direction, in the embodiment of the present invention, the rear side) while low-pressure compressing the air. .
The low pressure compressor 23 includes an annular blade support member 25 provided on the fan 19 and a plurality of stages of low pressure compression blade rows 27 provided on the outer peripheral portion of the blade support member 25 along the engine flow path 5. , The engine flow path 7 inside the second engine case 5
A plurality of stages of low-pressure compression moving blade rows 27 and a plurality of low-pressure compression low-pressure stationary blades 29 provided alternately are provided. Here, the low pressure compression blade row 27 is composed of a plurality of low pressure compression blades provided in the circumferential direction, and the low pressure compression stationary blade row 29 is composed of a plurality of low pressure compression blades provided in the circumferential direction. It is a thing.

A high pressure compressor 31 is provided downstream of the low pressure compressor 23 in the engine flow path 7, and the high pressure compressor 31 compresses the low pressure compressed air to a high pressure and sends it to the downstream side. is there. This high-pressure compressor 31 includes a plurality of stages of high-pressure compression blade rows 33 provided on the high-pressure turbine shaft 15 along the engine flow path 7, and a plurality of stages on the inside of the second engine case 5 along the engine flow path 7. High pressure compression blade row 3
3 and a plurality of high-pressure compression vane rows 35 alternately provided. Here, the high-pressure compression blade row 33 is composed of a plurality of high-pressure compression blades provided in the circumferential direction, and the high-pressure compression stationary blade row 35 is composed of a plurality of high-pressure compression stationary blades provided in the circumferential direction. It is a thing.

An annular combustion chamber 37 is provided downstream of the high-pressure compressor 29 in the engine flow path 7. The combustion chamber 37 burns fuel in compressed air to generate high-temperature and high-pressure combustion gas. It is what is generated.

A high-pressure turbine 39 is provided on the downstream side of the combustion chamber 37 in the engine flow path 7. The high-pressure turbine 39 drives the high-pressure turbine shaft 15 to rotate by the expansion of high-pressure and high-pressure combustion gas. . This high-pressure turbine 39 has a high-pressure turbine shaft 15 and an engine flow path 7
A plurality of stages of high-pressure turbine rotor blades 41 provided along the engine passage 7 and rotated by high-temperature and high-pressure combustion gas, and a plurality of stages of high-pressure turbine rotor blades 41 inside the second engine case 5 along the engine flow path 7. It is provided with a plurality of stages of high-pressure turbine vane rows 43 alternately provided. Here, the high pressure turbine rotor blade row 41 is composed of a plurality of high pressure turbine rotor blades provided in the circumferential direction, and the high pressure turbine stationary blade row 45 is composed of a plurality of high pressure turbine stator blades provided in the circumferential direction. It is a thing.

High-pressure turbine 39 in the engine flow path 7
A low-pressure turbine 45 is provided downstream of the low-pressure turbine 45. The low-pressure turbine 45 rotates the low-pressure turbine shaft 11 by expanding high-temperature and high-pressure combustion gas. The low-pressure turbine 45 includes an annular blade support member 47 provided on the low-pressure turbine shaft 11 and a plurality of high-temperature and high-pressure combustion gases provided on the outer peripheral portion of the blade support member 47 along the engine flow path 7. Low pressure turbine rotor blade row 49 in stages,
Inside the second engine case 5, a plurality of stages of low-pressure turbine rotor blade rows 49 and a plurality of stages of low-pressure turbine stationary blade rows 51 that are alternately provided are provided along the engine flow path 7. Here, the low-pressure turbine rotor blade row 49 is composed of a plurality of low-pressure turbine rotor blades provided in the circumferential direction, and the low-pressure turbine stator blade row 51 is composed of a plurality of low-pressure turbine stator blades provided in the circumferential direction. It is a thing.

At the rear part of the second engine case 5, there is provided a tail cone 53 for guiding the high temperature and high pressure combustion gas ejected from the downstream part of the engine flow path 7. The high-temperature and high-pressure combustion gas ejected from the downstream portion of the engine flow passage 7 is wrapped with cold air ejected from the downstream portion of the bypass flow passage 9.

The operation of the jet engine 1 having the above structure will be briefly described as follows.

That is, the high pressure turbine shaft 15 is rotated by the drive of an appropriate starter device (not shown), and the high pressure compressor blade rows 33 of a plurality of stages are integrally rotated. The compressed compressed air flows into the combustion chamber 37. Next, by burning the fuel in the compressed air in the combustion chamber 37,
Generates and expands high temperature and high pressure combustion gas. When the rotation speed of the high-pressure turbine shaft 15 reaches a predetermined rotation speed, the drive of the starter device is stopped.

By expanding the high-temperature and high-pressure combustion gas, the multistage high pressure turbine rotor blade row 41 rotates, the high pressure turbine 39 rotates the high pressure turbine shaft 15, and the multistage low pressure turbine rotor blade row 49. Rotates to rotate the low pressure turbine shaft 11 by the low pressure turbine 45. As a result, the fan 19 and the plurality of stages of low-pressure compression blade rows 27 are rotated integrally with the low-pressure turbine shaft 11, and the air is taken into the engine flow path 7 and the bypass flow path 9 by the low-pressure compressor 23. Is compressed at low pressure, and the high-pressure compression blade rows 41 of multiple stages are integrally rotated with the high-pressure turbine shaft 15 so that the high-pressure compressor 31 compresses the air at high pressure. Flows into 37.

Further, the combustion gas generated by rotating the multi-stage high pressure turbine rotor blade row 41 and the multi-stage low pressure turbine rotor blade row 49 is ejected from the downstream portion of the engine flow path 7 to obtain a propulsive force. . Here, since cold air is jetted from the downstream portion of the bypass passage 9 and the combustion gas is enclosed by the cold air, noise due to jetting of the combustion gas can be suppressed, and fuel consumption can be reduced.

In order to extract power from the rotational force of the high pressure turbine shaft 15, the jet engine 1 has the following structure.

That is, as shown in FIGS. 1 and 3, a mounting hole 55 is formed in the rear portion of the first engine case 3, and the base end of the cylindrical housing 57 is formed at the edge of the mounting hole 55. The parts are attached via a plurality of attachment bolts 59. Here, the base end portion of the housing 57 is a flange, and the plurality of mounting bolts 59 penetrate the base end portion (flange) of the housing 57. Also, the housing 5
The tip portion of 7 can be inserted into a stepped insertion hole 61 formed in the rear portion of the second engine case 5, and the insertion hole 61 is located closer to the high-pressure turbine shaft 15 side than the mounting hole 55. A strut 63 that covers the housing 57 is provided between the first engine case 3 and the second engine case 5.

A power extraction shaft 65 is rotatably provided in the housing 57 via a bearing 67, and a tip portion of the power extraction shaft 65 projects toward the high pressure turbine shaft 15 side with respect to the housing 57. Also, the housing 57
When the tip of the is inserted into the insertion hole 61, the high pressure turbine shaft 15
In order to connect the high pressure turbine shaft 15 to the second engine case 5, a connecting member 6 is provided near the rear end of the high pressure turbine shaft 15.
9 is rotatably provided via a plurality of bearings 71. When the tip of the housing 57 is inserted into the insertion hole 61, the tip of the power extraction shaft 65 is spline-fitted to the connecting member 69. The connecting member 69 is operatively connected to the high-pressure turbine shaft 15 via the driven bevel gear 73 and the drive bevel gear 75. Furthermore, the power extraction shaft 6
An input side of the speed reducing mechanism 77 is connected to the base end of the speed reducer 5, and an output side of the speed reducing mechanism 77 is connected to a driving device (not shown) such as a lubricating oil supply pump.

Further, as shown in FIG. 4, a plurality of (four in the embodiment of the present invention) hole fitting recesses 79 are formed on the inner peripheral surface of the insertion hole 61, and the housing is formed. A plurality of (four in the embodiment of the present invention) fitting protrusions 81 for housing, which are respectively fitted into the fitting recesses 79 for holes, are formed on the outer peripheral surface of the tip portion of 57. Further, when a rotational torque is applied to the housing 57 in one direction (the arrow direction in FIG. 4) with the distal end portion of the housing 57 inserted in the insertion hole 61, the pressing surface 8 of the housing fitting convex portion 81.
1f presses the pressed surface 79f of the hole fitting recess 79, and the power extraction shaft 65 is centered so that the center of the housing 57 coincides with the center of the insertion hole 61.

Here, the number of hole fitting concave portions 79 and the number of housing fitting convex portions 81 are not limited to four, but may be two or more (desirably three or more). Further, instead of forming the hole fitting concave portion 79 and the housing fitting convex portion 81, a plurality of (preferably three or more) hole fitting convex portions are formed on the inner peripheral surface of the insertion hole 61. In addition, a plurality of (preferably three or more) housing fitting recesses that fit into the hole fitting projections may be formed on the outer peripheral surface of the distal end of the housing 57. Further, the pressed surface 79f of the hole fitting recess 79 (or the pressed surface of the hole fitting projection) and the pressing surface 81f of the housing fitting projection 81 (or the pressing surface of the housing fitting recess). ) Each have an involute shape, a female involute spline is formed on the inner peripheral surface of the insertion hole 61, and the female involute spline is formed on the outer peripheral surface of the distal end portion of the housing 57. A male involute spline that fits a spline may be formed.

As shown in FIGS. 5 and 1, the housing 5
7 is provided with a rotational torque in one direction (arrow direction in FIG. 5), a protrusion 83 is provided on the base end portion (flange) of the housing 57, and the base end portion of the housing 57 in the first engine case 3 is provided. Fixing member 8 fixed in the vicinity
5 is a torque bolt 8 capable of pushing the projection 83 in one direction.
7 are provided so as to be screwed together. Note that, without using the protrusion 83 and the torque bolt 87, as shown in FIG. 6, a notch 89 formed in the base end portion of the housing 57.
Is fitted to a fitting member 91 fixed to the first engine case 3, and a wedge 93 is driven between the notch 89 and the fitting member 91, whereby the housing 57 is unidirectionally (direction of arrow in FIG. 6). The rotation torque may be applied.

A cover member (not shown) that can be opened and closed is provided in the first engine case 3 in order to mount and maintain the power extraction shaft 65, the housing 57 and the like.

Next, the operation of the embodiment of the present invention will be described.

The front end of the housing 57 is inserted into the insertion hole 61 and the power extraction shaft 65 is spline-fitted to the connecting member 69, whereby the front end of the power extraction shaft 65 is driven and driven by a bevel gear 73 and a driving bevel gear 75. Is connected to the high-pressure turbine shaft 15 via. Then, with the tip of the housing 57 being inserted into the insertion hole 61, the torque bolt 87 is screwed to push out the protrusion 83 in one direction to move the housing 57.
By applying a rotational torque in one direction, the pressing surface 81f of the housing fitting convex portion 81 (or the pressing surface of the housing fitting concave portion) is pressed by the hole fitting concave portion 79f.
(Or the pressed surface of the hole fitting protrusion) is pressed. As a result, the tip of the housing 57 is pressed in one direction on the inner peripheral surface of the insertion hole 61, and the support rigidity of the housing 57 can be increased. Also, the housing 57
By applying a rotating torque in one direction to the housing 5,
The power extraction shaft 65 is aligned such that the center of 7 coincides with the center of the insertion hole.

Then, by tightening the plurality of mounting bolts 59, the base end portion of the housing 57 is attached to the edge portion of the mounting hole 55 in the first engine case 3.

As described above, the preparation for obtaining power from the rotation of the high pressure turbine shaft 15 by the power extraction shaft 65 is completed.

After the preparation is completed, as described above,
The high pressure turbine shaft 15 is rotated by expanding the high temperature and high pressure combustion gas. As a result, the power extraction shaft 6
It is possible to rotate 5 in cooperation with the high-pressure turbine shaft 15, in other words, obtain power from the rotation of the high-pressure turbine shaft 15 and transmit the power to the drive device.

When the housing 57 supporting the power extraction shaft 65 is to be removed from the engine cases 3 and 5 for reasons such as maintenance, a plurality of mounting bolts 59 are required.
Is loosened, the fixed state of the base end portion of the housing 57 with respect to the first engine case 3 is released. next,
Rotating torque is applied to the housing 57 in the other direction (direction opposite to the arrow direction in FIGS. 4 to 6) to press the pressing surface 81f of the housing fitting projection 81 (or the pressing surface of the housing fitting recess) and the hole. The pressed state of the pressed surface 79f of the fitting recess 79 (or the pressed surface of the hole fitting projection) is released. Then, the tip end of the power extraction shaft 65 is removed from the connecting member 69, the tip end of the housing 57 is removed from the insertion hole 61, and the housing 57 supporting the power extraction shaft 65 is removed from the engine cases 3 and 5. As described above, according to the embodiment of the present invention, the tip end portion of the housing 57 is pressed in one direction on the inner peripheral surface of the insertion hole 61, so that the supporting rigidity of the housing 57 can be increased, so By suppressing the resonance of the housing 57 due to the rotation of the extraction shaft 65, the high pressure turbine shaft 15
It becomes easy to stably extract the power from. Also,
By applying a rotational torque to the housing in one direction while the distal end of the housing 57 is inserted into the insertion hole, the distal end of the housing 57 is pressed in the inner peripheral surface of the insertion hole 61 in one direction. Since the center of the housing 57 can be aligned with the center of the insertion hole 61 to align the power extraction shaft 65, the power extraction shaft 65 can be prevented from shaking and the power extraction from the high-pressure turbine shaft 15 can be more stable.

The present invention is not limited to the above description of the embodiments of the present invention, and the structure of the present invention is used in a gas turbine engine other than the jet engine 1, or in place of the high pressure turbine shaft 15, a low pressure turbine. The present invention can be implemented in various other modes by making appropriate changes such as extracting power from the shaft 11.

[0043]

According to the invention described in any one of claims 1 to 3, the distal end portion of the housing is pressed in one direction on the inner peripheral surface of the insertion hole. Since the support rigidity of the housing can be increased, resonance of the housing due to rotation of the power extraction shaft can be suppressed, and stable extraction of power from the turbine shaft can be facilitated.

According to the second or third aspect of the invention, the rotational torque is applied to the housing in one direction while the tip of the housing is inserted into the insertion hole, so that the housing is rotated. In addition to the tip portion being pressed in one direction on the inner peripheral surface of the insertion hole, the center of the housing can be aligned with the center of the insertion hole to align the power extraction shaft. The power extraction from the turbine shaft is made more stable by eliminating the blurring.

[Brief description of drawings]

FIG. 1 is an enlarged view of an arrow I in FIG.

FIG. 2 is a sectional view of a jet engine according to an embodiment of the present invention.

FIG. 3 is an enlarged view of an arrow II in FIG.

FIG. 4 is an enlarged view taken along line III-III in FIG.

5 is an enlarged view taken along line IV-IV in FIG.

FIG. 6 is a diagram showing another mode in which a rotational torque is applied to the housing.

[Explanation of symbols]

1 Jet engine 3 First engine case 5 Second engine case 11 High-pressure turbine shaft 15 Low pressure turbine shaft 55 Mounting hole 57 housing 61 insertion hole 65 Power extraction shaft 79 Housing projection 81 hole fitting recess 83 protrusions 85 Torque bolt

Claims (3)

[Claims] 1. A gas turbine engine in which a turbine shaft in an engine case is rotated by expanding combustion gas of high temperature and high pressure, wherein a base end portion is attached to an edge portion of an attachment hole formed in the engine case, and a tip end is attached. A tubular housing having a portion that can be inserted into an insertion hole formed on the turbine shaft side of the mounting hole in the engine case; and a rotatably provided on the housing, the tip side of which is the turbine shaft side of the housing. It protrudes to
A power extraction shaft configured to be connected to the turbine shaft when the tip portion of the housing is inserted into the insertion hole, and a hole fitting concave portion or a hole fitting convex portion formed on an inner peripheral surface of the insertion hole. And a housing fitting convex portion that is formed on the outer peripheral surface of the distal end portion of the housing and that fits into the hole fitting concave portion, or a housing fitting concave portion that fits into the hole fitting convex portion. When the distal end of the housing is inserted into the insertion hole and a rotational torque is applied to the housing in one direction, the pressing surface of the housing fitting convex portion or the housing fitting concave portion is A gas turbine engine, which is configured to press the pressed surface of the hole fitting concave portion or the pressed surface of the hole fitting convex portion. 2. A plurality of the hole fitting recesses or the hole fitting projections, a plurality of the housing fitting projections or the housing fitting recesses, and a front end portion of the housing being the insertion hole. When a rotational torque is applied to the housing in one direction while being inserted into the housing, the pressing surface of the housing fitting convex portion or the housing fitting concave portion is pressed against the hole fitting concave portion. Alternatively, in addition to pressing the pressed surface of the hole fitting projection, the center of the housing matches the center of the insertion hole so that the power extraction shaft is aligned. The gas turbine engine according to claim 1. 3. The gas turbine engine according to claim 1 or 2, further comprising a torque applying unit that applies a rotational torque to the housing in one direction.