JPH04303135A - Gas turbine engine - Google Patents

Abstract

PURPOSE:To compose a scroll, a back plate, a high pressure turbine shroud, and a nozzle vane of a gas turbine engine to be separate from each other, and integrate them securely in a condition where they are less likely to have effects of a thermal stress. CONSTITUTION:A back plate 21, a nozzle vane 25, and a high pressure turbine shroud 22 are laid one on top of another in the axial direction, and a scroll 24 is disposed at their outer circumferences. A pressure member 75 energized in the axial direction by resiliency of a spring 74 has two pressure parts 751, 752, the scroll 24 is pressed by the outer side pressure part 751, and the high pressure turbine shroud 22 is pressed by the inner side pressure part 752, so they are positioned and fixed. The back plate 21, high pressure turbine shroud 22, nozzle vane 25, and pressure members 75 are mutually positioned by pins 71, 72 disposed in the axial direction.

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 in which a back plate, a nozzle vane, and a shroud are stacked in the axial direction inside a casing, and a scroll is disposed around the outer periphery of the back plate, nozzle vane, and shroud.

0002

[Prior Art] In such a gas turbine engine,
It is known that a back plate, a high-pressure turbine shroud, and a nozzle vane, which are superimposed on the inner circumference of the scroll, are integrated by elastically pressing the outer circumference of a scroll that is divided into two parts in the front-rear direction ( (See Utility Model Application Publication No. 1-113140).

0003

[Problems to be Solved by the Invention] However, since the above-mentioned conventional device elastically presses the outer periphery of the scroll, which is divided into two parts in the front-rear direction, the pressing force is not sufficiently transmitted to the inner periphery of the scroll. As a result, there is a possibility that the back plate, high pressure turbine shroud, and nozzle vane, which are superimposed on the inner peripheral portion of the scroll, may become unstable. In order to prevent this, the above-mentioned members may be firmly connected and integrated, but if this is done, there is a problem that a large stress is generated in the overlapped portion due to the difference in the amount of thermal expansion of each member.

The present invention has been made in view of the above-mentioned circumstances, and it applies an appropriate elastic force to the scroll, back plate, nozzle vane, and shroud of a gas turbine engine to ensure that they are integrated, and at the same time, reduces the heat generated by them. The purpose is to reduce the effects of expansion.

[0005]

[Means for Solving the Problems] In order to achieve the above object, the present invention provides a gas turbine engine in which a back plate, a nozzle vane, and a shroud are superimposed in the axial direction inside a casing, and a scroll is disposed around the outer periphery of the back plate, nozzle vane, and shroud. The scroll, the back plate, the nozzle vane, and the shroud are each formed separately, elastically biased in the axial direction by a pressing member having at least two or more pressing portions, and the nozzle vane is positioned as a width determining member. The first feature is that it is fixed.

In addition to the above-mentioned first feature, the present invention also provides that the nozzle vane is pinched from the front and back by the back plate and the shroud, and that one of the positioning members protruding from the front and rear of the nozzle vane is used as the back plate, and the other is used as the shroud. The second feature is that it is locked.

In addition to the first or second feature described above, the present invention has a third feature in that a pressing member applies a pressing force to at least the scroll and the shroud.

In addition to the third feature described above, the present invention has a fourth feature in that the pressing member is provided with two or more pressing portions spaced apart in the radial direction.

Further, in addition to the third or fourth feature described above, the present invention has a fifth feature that the pressing member is divided into a plurality of members disposed in the circumferential direction and in contact with each other. do.

[0010] In addition to the above-mentioned fifth feature, the present invention also provides that at least one of the plurality of divided pressing members:
A sixth feature is that the shroud is locked by a positioning member.

In addition to any one of the first to sixth features described above, the present invention has a seventh feature in that the scroll is divided into a plurality of sections by a cross section intersecting the combustion gas passage.

[0012] In addition to any one of the first to seventh features described above, the present invention has an eighth feature that the back plate is supported by the casing with a positioning key interposed therebetween.

[0013] In addition to the above-mentioned eighth feature, the present invention also provides that the positioning means includes guide grooves facing each other formed in the radial direction on the casing side and the back plate, respectively, and a rotating mechanism that engages with these guide grooves. The ninth feature is that it is composed of keys.

In addition to the above-mentioned first feature, the present invention has a tenth feature that the back plate is divided into a radially outer portion and a radially inner portion.

In addition to the above-mentioned tenth feature, the present invention has an eleventh feature in that a sealing member is interposed between the radially outer portion and the radially inner portion of the back plate.

[0016]

Embodiments Hereinafter, embodiments of the present invention will be explained based on the drawings.

FIGS. 1 and 2 schematically show the structure of a gas turbine engine according to a first embodiment of the present invention. The two-shaft gas turbine engine G includes a bottomed cylindrical outer casing 1, an annular heat exchanger housing 2 connected to the rear opening of the outer casing 1, and an exhaust that covers the rear part of the heat exchanger housing 2. housing 3
Equipped with. An intake passage 6 equipped with an air cleaner 4 and a silencer 5 is connected to the front part of the outer casing 1, and a reducer box 7 is disposed in the center of the exhaust housing 3. An exhaust duct 8 is connected.

A centrifugal compressor 9 for compressing the air taken in from the intake passage 6 and a centrifugal high-pressure turbine 10 for driving the compressor 9 are disposed before and after the central opening formed in the outer casing 1. At the same time, an axial-flow type low-pressure turbine 11 for extracting output is disposed behind the outer casing 1, and combustion gas for driving the high-pressure turbine 10 and the low-pressure turbine 11 is provided in the upper space of the outer casing 1. A combustor 12 is provided to generate the fuel. Further, inside the heat exchanger housing 2, an annular heat exchanger 13 for recovering the thermal energy of the combustion gas that has passed through the turbines 10 and 11 and heating the intake air is arranged around the reducer box 7. Inside the reducer box 7 is a planetary gear type reducer 14 that reduces the output of the low pressure turbine 11 and takes it out to the outside.
will be placed.

A high-pressure turbine shaft 16 is rotatably supported in the center of the compressor casing 15 provided in the outer casing 1, and a compressor rotor 17 having a large number of blades formed on the outer periphery is fixed to the high-pressure turbine shaft 16. Ru. The air sucked into the compressor casing 15 from the intake passage 6 is compressed by the compressor rotor 17 and is supplied rearward through a radial air passage 19 formed between the outer casing 1 and the inner casing 18. . Note that the front end of the high-pressure turbine shaft 16 is connected to auxiliary equipment such as a generator and a starter housed in an auxiliary equipment housing (not shown).

A high-pressure turbine rotor 20 made of ceramics and having a large number of blades formed on its outer periphery is fixed to the rear end of the high-pressure turbine shaft 16, and the high-pressure turbine rotor 20 is located between a back plate 21 made of ceramics and a high-pressure turbine shroud 22. will be stored in. A scroll 24 also made of ceramics is disposed outside the high-pressure turbine shroud 22 and is connected to the combustor 12 via a transient duct 23 made of ceramics.
A plurality of nozzle vanes 25 are provided between the inner circumference of the high-pressure turbine rotor 20 and the outer circumference of the high-pressure turbine rotor 20 . scroll 24
is supported from the outer periphery by a plurality of support mechanisms 26, and the transient duct 24 is supported by other support mechanisms 27, 28.
Supported by

A collector housing 29 is provided at the front end of the heat exchanger housing 2 connected to the rear part of the outer casing 1.
is supported, and a low pressure turbine shaft 30 is supported at the center thereof. A ceramic low-pressure turbine rotor 31 is fixed to the tip of the low-pressure turbine shaft 30, and a large number of blades formed on its outer circumference fit into the inner surface of a low-pressure turbine shroud 32. The low pressure turbine shroud 31 and the high pressure turbine shroud 22 are connected by a low pressure turbine duct 34 having a variable stator vane 33 at its rear end. The low pressure turbine shaft 30 is connected to an output shaft 35 via the reduction gear 14.

An arc-shaped opening 291 is formed in the upper half of the collector housing 29, through which air flows from the air passage 19 to the upper part of the exhaust housing 3, passes through the upper half of the heat exchanger 13, and is heated. Air flows through this opening 2
It is supplied to the inside of the inner casing 18 via 91. On the other hand, in the lower half of the collector housing 29, exhaust gas that has passed through the low pressure turbine shroud 32 is connected to a heat exchanger 13.
An exhaust gas passage 292 is formed to lead to the lower half of the exhaust gas.

A ring gear 36 is attached to the outer periphery of the heat exchanger 13 over 360 degrees, and a flat support surface formed at the front of the ring gear 36 is connected to a plurality of guide rollers provided on the inner periphery of the heat exchanger housing 2. It is rotatably supported by 37. A pinion 39 that meshes with the ring gear 36 is fixed to a rotating shaft 38 that supports one guide roller 37, and the heat exchanger 13 is rotationally driven by rotating the rotating shaft 38 with a heat exchanger drive motor 40. Ru.

As is clear from FIG. 2, the scroll 24 includes a rotating shaft of the high-pressure turbine 10 and is divided into four pieces by two mutually perpendicular surfaces, a first piece 41 and a second piece.
It is composed of a piece 42, a third piece 43, and a fourth piece 44. That is, the two end faces of each piece 41 to 44 are formed into a simple plane that makes an angle of 90 degrees to each other, and each piece 41 to 44 is held together by abutting against each other at joint surfaces a, b, c, and d. Ru.

Next, a support structure for the scroll 24 using the support mechanism 26 will be explained based on FIGS. 3 to 5. 8
The support mechanism 26 presses two locations of each of the pieces 41 to 44 inward in the radial direction in order to bring the joint surfaces a to d of the four pieces 41 to 44 into close contact with each other. All other structures are the same except for the length. That is, the support mechanism 26 includes a support shaft 45 having a pressing member 46 attached to its tip, and a cylindrical support member 47 that supports a columnar portion 451 formed at the base end of the support shaft 45 so as to be able to slide in the axial direction. , a spring seat 48 screwed onto the outer end of the support member 47; and a spring compressed between the spring seat 48 and the cylindrical portion 451 to bias the support shaft 45 radially inward toward the scroll 24. It consists of 49 pieces.

A flat receiving portion 241 is formed on the outer periphery of the piece 41 of the scroll 26 as an example, and this receiving portion 241 has an opening 501 of the support plate 50.
The pressure-receiving member 51, which is loosely fitted and prevented from falling off, comes into contact with it. A conical pressure receiving surface 511 is formed on the outside of the pressure receiving member 51, while a hemispherical pressing surface 461 that engages with the pressure receiving surface 511 is formed on the pressing member 46, thereby making contact with the pressing surface 461. Surface 511 is in line contact along the circumference. As a result, due to thermal expansion of each part, the pressing member 46
Even if an angle change occurs between the pressure-receiving member 49 and the conical pressure-receiving surface 511 and the hemispherical pressing surface 461, stable line contact is always obtained, so the surface pressure at the contact portion can be kept low. A scroll 24 can be supported.

Flange 471 formed on support member 47
is fixed to the boss 11 of the outer casing 1 with a bolt 52, and its inner end extends through the inner casing 18 and is supported. That is, the inner casing 18
An annular slider 54 is attached to a guide member 53 provided in an opening 181 so as to be slightly movable, and a support member is attached to a circumferential edge 541 formed by two conical surfaces on the inner periphery of the slider 54. The outer periphery of 47 comes into contact. Therefore, the radial displacement of the scroll 24 and the inner casing 1 due to thermal expansion is absorbed by the expansion and contraction of the spring 49, and the scroll 24, the outer casing 1,
The axial or circumferential displacement of the inner casing 18 is determined by the guide member 53 of the slider 54 and the support member 4.
Absorbed by sliding against 7.

[0028] Since the four pieces 41 to 44 are each supported by eight independent support mechanisms 26,
No matter how the pieces 41 to 44 thermally expand, the scroll 24 can be reliably supported without generating excessive stress.

As is clear from FIG. 2, the inlet end and the outlet end of the transient duct 23 are cut along a plane making an angle of 90° to each other, thereby facilitating manufacturing and improving processing accuracy. The outlet end of the transient duct 23 is slidably abutted against the inlet end of the first piece 41 of the scroll 24, and is pushed in opposite directions by a pair of support mechanisms 27 and 28 provided in the outer casing 1. is retained.

As shown in FIG. 6, the support mechanism 27 of the transient duct 23 has a support shaft 45 supported by the outer casing 1 via a support member 47, and a support shaft 45 that is connected to the transient duct 23 via a pressing member 46 and a pressure receiving member 51. It is configured to press the formed receiving portion 231 . Since the structure of this support mechanism 27 is substantially the same as the support mechanism 26 of the scroll 24 described above, the same reference numerals as those of the components of the support mechanism 26 described above are given to its components, thereby omitting redundant explanation. .

As shown in FIGS. 7 and 8, the other support mechanism 28 of the transient duct 23 has a slightly different construction than previously described. That is, the support shaft 45 has a flange 453 formed at its base end.
is fixed to the boss 11 of the outer casing 1 with bolts 52. A pressure receiving member 56 having a groove 561 into which a cylindrical roller 55 is fitted is rotatably supported in the hole 233 of the receiving portion 232 formed in the transient duct 23 via a pin 562 or a protrusion. On the other hand, the roller 55 is rotatably fitted between a pair of side walls 452 formed at the tip of the support shaft 45, and the retainer 57
is maintained by As a result, the support shaft 45
The displacement around the axis of the roller 55 is absorbed by the rotation of the pressure receiving member 56 around the pin 561, and the displacement around the axis of the roller 55 is absorbed by the rotation of the support shaft 45 and the pressure receiving member 56 with respect to the roller 55. absorbed,
Further, displacement in a direction perpendicular to the axis of the support shaft 45 is absorbed by the roller 55 rolling within the groove 561 of the pressure receiving member 56.

As is clear from FIG. 2, the support mechanism 2
7 is inclined with respect to the joint surface of the first piece 41 of the scroll 24 and the transient duct 23, and the component force F1' of the pressing force F1 is equal to the reaction force F2 received from the support mechanism 28. By balancing, the transient duct 23 is held in a stable state.

Next, the means for fixing the scroll 24, back plate 21, and high pressure turbine shroud 22 in the axial direction will be explained based on FIGS. 9 to 11. Three roller grooves 581 extending radially around the high-pressure turbine shaft 16 are formed at 120° intervals on the rear surface of the metal base plate 58 attached to the center of the inner casing 18 (see FIG. 2). A ceramic roller 60 is housed inside the roller 60 while being held by a retainer 59 . The back plate 21 made of ceramics and arranged to face the rear surface of the base plate 58 is composed of an annular back plate outer 61 and a back plate inner 62 arranged radially inside thereof. A roller groove 611 is formed at the outer end of the front surface of the back plate outer 61 in the radial direction, with which the roller 60 accommodated in the roller groove 581 of the base plate 58 engages. As a result, the back plate 21 is centered with respect to the base plate 58 via the roller 60, and radial displacement between the base plate 58 and the back plate 21 due to the difference in coefficient of thermal expansion is absorbed.

[0034] Inside the base plate 58, an air passage 582 is formed in the radial direction and communicates with the air passage 19 formed between the outer casing 1 and the inner casing 18. A pair of partition members 63 and 64 are arranged between the inner periphery of the base plate 58 and the compressor rotor 17, and the air chamber 65 defined between the partition members 63 and 64 and the air passage 582 of the base plate 58 form an orifice. 583. and the partition wall member 63,
64 and the compressor rotor 17 are formed with labyrinths 171 and 172, respectively.

An annular seal plate 66 and the inner periphery of the back plate inner 62 are tightened together with a nut 67 at the lower end of the rear partition member 63. A seal ring 68 having a split opening expanding outward in the radial direction is installed between the upper ends of the seal plate 66 and the back plate inner 62 . By bringing them into contact with each other, the space between the back plate outer 61 and the back plate inner 62 is sealed.

Thus, the air that reaches the air chamber 65 from the air passage 19 formed between the outer casing 1 and the inner casing 18 through the air passage 582 and the orifice 583 of the base plate 58 and the tip of the compressor rotor 17 The air that has reached the air chamber 65 passes through the labyrinths 171 and 172 and reaches the high pressure turbine shaft 1.
6, it passes through the rear surface of the back plate inner 62 and joins the combustion gas acting on the high pressure turbine rotor 20. Therefore, the back plate inner 62 that comes into contact with the cooling air is kept at a relatively low temperature and has a small coefficient of thermal expansion. On the other hand, the high temperature combustion gas supplied from the scroll 24 comes into direct contact with the back plate outer 61, and its coefficient of thermal expansion becomes large. In this way, the temperature of the back plate 21 is different between the inner part and the outer part,
Since the portions having different temperatures are divided into separate members, the back plate inner 62 and the back plate outer 61, generation of large thermal stress on the back plate 21 is prevented. At this time, a gap is generated between the back plate outer 61 and the back plate inner 62 due to the difference in thermal expansion, but this gap is sealed by the seal ring 68, and the low pressure side from the front surface of the back plate 21 to the low pressure side of the rear surface of the back plate 21 is sealed. Air leakage to the sides is prevented.

The step portion 221 formed at the rear end of the high-pressure turbine shroud 22 and the step portion 341 formed at the front end of the low-pressure turbine duct 34 are loosely connected by a spigot joint, and an annular spring retainer is attached to the outer periphery of the step portion 341 of the low-pressure turbine duct 34. The inner periphery of 69 is engaged. A seal ring 70 is installed in a space defined by the high-pressure turbine shroud 22, the low-pressure turbine duct 34, and the spring retainer 69. Due to its own elasticity, the inner peripheral surface of the seal ring 70 contacts and seals the outer peripheral surface of the stepped portion 221 of the high-pressure turbine shroud 22, and at the same time seals the inside of the inner casing 18, which is the high-pressure side, and the low-pressure turbine duct 3, which is the low-pressure side.
Due to the pressure difference inside 4, it comes into contact with the front end surface of the low pressure turbine duct 34 and seals it. Thereby, the joint can be sealed while absorbing displacement due to thermal expansion of the high-pressure turbine shroud 22 and the low-pressure turbine duct 34.

In the annular space sandwiched between the back plate 21 and the high-pressure turbine shroud 22 in the front-rear direction and between the high-pressure turbine rotor 20 and the shroud 24 in the radial direction, there are a relatively small number of simple-shaped plates, namely six pieces. A nozzle vane 25 is provided. The front part of each nozzle vane 25 is fixed by a pin 71 passing through the high pressure turbine shroud 22, and the rear part is fixed to the back plate 22.
It is fixed by another pin 72 that engages with 1. By simplifying the shape of the nozzle vane 25 and reducing the number of nozzle vanes in this way, it is possible to reduce the number of parts and simplify manufacturing while maintaining the same pitch code ratio as a small number of nozzle vanes. Stress can be reduced. Further, since the nozzle vane 25 is sandwiched between the back plate 21 and the shroud 22 and connected with pins 71 and 72, the nozzle vane 25 is attached to the back plate 22.
It functions as a link connecting the back plate 21 and the shroud 22, and can effectively absorb displacement due to thermal expansion of the back plate 21 and the shroud 22.

On the other hand, the scroll 24 is supported on the outer periphery of the back plate 21 and the outer periphery of the high-pressure turbine shroud 22 by bringing the front edge of the inner periphery of the scroll 24 into contact with the outer periphery of the back plate 21 via a detent pin 73. At the same time, the rear edge is pressed by a ceramic pressing member 75 biased by a spring 74 compressed between the spring retainer 69 and the spring retainer 69. The pressing members 75 are generally trapezoidal members, and 24 of them are arranged in the circumferential direction and contact each other closely at contact surfaces extending in the radial direction, and each of them is separately biased by the spring 74. Ru. Then, a pressing protrusion 751 having an arc-shaped contact surface formed on the outside in the radial direction of each pressing member 75 presses the inner circumference of the scroll 24, and a pressing projection 751 having an arc-shaped contact surface formed on the inside in the radial direction presses the inner circumference of the scroll 24. A protrusion 752 presses against the back of the high pressure turbine shroud 22. At this time,
Six pins 71 passing through the high pressure turbine shroud 22
engages with the six pressing members 75 at corresponding positions and fixes those pressing members 75. Further, the other 18 pressing members 75 that are not engaged with the pin 71 are indirectly positioned via the pressing members 75 fixed by the pin 71, and both pressing protrusions 751 and 752 are formed on the scroll 24. By abutting the stepped portion 242 and the stepped portion 222 formed on the high-pressure turbine shroud 22, it is also positioned in the radial direction.

Thus, the elastic force of the spring 74 is transmitted along the path of the pressing protrusion 751 on the outside of the pressing member 75 -> the scroll 24 -> the back plate 21, and the elastic force is transmitted through the pressing process on the inside of the pressing member 75. It is transmitted along the path of protrusion 752 → high pressure turbine shroud 22 → nozzle vane 25 → back plate 21. As a result, in order to simplify the part shape and reduce thermal stress, the back plate 21
Even if the nozzle vane 25, turbine shroud 22, and scroll 24 are formed separately, they can be held together by the pressing force of the pressing member 75. At this time, the pressing protrusions 7 on the outside and inside of the pressing member 75
The load of the spring 74 applied to the springs 51 and 752 can be changed to an arbitrary ratio by moving the connection portion of the spring 74 to the pressing member 75, that is, the position of the spring receiving protrusion 753 in the radial direction.

Next, the structure of the combustor 12 will be explained based on FIG. 12. Outer casing 1 and inner casing 1
A flange 761 formed at the rear end of the radially outer combustor casing 76 has a flange 761 formed at the rear end of the cylindrical main body casing 78. 781 is fixed with bolt 79. As a result, an air passage 1 is formed between the outer casing 1 and the inner casing 18 between the radially inner combustor casing 77 and the main body casing 78.
A cooling air passage 80 is formed which communicates with the cooling air passage 9 . A fuel injection nozzle 82 is attached to the tip of the main body casing 78 via a nozzle support member 81, and a burner liner 83 connected to the transient duct 23 is provided in front of the nozzle. The tip of an igniter 84 supported by the outer casing 1 projects inside the burner liner 83.

Next, the structure of the combustor 12 is shown in FIGS.
5 will be explained in more detail. The fixing member 85 welded to the tip of the inner combustor casing 77 and the main body casing 7
Reverse threads are formed at the tips of the liners 8, and an annular liner support member 86 is screwed onto these reverse threads. Three flanges 861 are provided at 120° intervals on the inner circumference of the liner support member 86.
Three flanges 831 projecting from the outer periphery of the rear end of the burner liner 83 at 120° intervals are bayonet connected to this flange 861 . That is, Figure 1
5, the flange 831 of the burner liner 83
After inserting the burner liner 83 into the liner support member 86 by aligning the position of the notch of the flange 861 of the liner support member 86 with the position of the notch of the flange 861 of the liner support member 86, the Burner liner 83 is bayonet coupled to liner support member 86 . At this time, the rear end of the burner liner 83 is pressed by a blocking member 88 biased by a spring 87 compressed between it and the nozzle support member 81, and the flange 831
is pressed against the rear surface of the flange 861 of the liner support member 86. In order to prevent rotation of the burner liner 83, the burner liner 83 and the blocking member 88 are connected to each other by a pin 90 so that they cannot rotate relative to each other, and the blocking member 88 and the nozzle support member 81 are connected to each other by a pin 89 so that they cannot rotate relative to each other. Ru. With the above configuration, the fuel injection nozzle 82 and the burner liner 8
By simply inserting the main body casing 78 integrally supporting the combustion chambers 3 into the combustor casings 76 and 77 from the outside of the outer casing 1, it can be easily attached and detached.

Nozzle tip 821 of fuel injection nozzle 82
A swirler 91 having a plurality of blades is disposed between the burner liner 83 and the inner periphery of the base of the burner liner 83 . A cooling air passage 80 formed between the combustor casing 77 and the main body casing 78 communicates with the inside of the blocking member 88 through a through hole 782, and from there communicates with the annular space between the fuel injection nozzle 82 and the swirler 91. It communicates with the inside of the burner liner 83 through. As a result, the fuel injection nozzle 82 and the spring 87 are effectively cooled by the low temperature air (approximately 200° C.) introduced from the cooling air passage 80, thereby preventing coking (carbonization) of the fuel and deterioration of the spring 87. Can be done. Further, a portion of this low-temperature air is guided from the through hole 822 to the nozzle tip 821 and is also used as fuel blast air.

On the other hand, the high temperature air (approximately 800° C.) inside the inner casing 18 flows through the swirler 91 through three openings 92 (see FIGS. 13 and 14) formed between the liner support member 86 and the burner liner 83. The air is guided into a swirling flow and introduced into the burner liner 83 as primary air. At this time, the partition wall member 88 prevents mixing of high temperature air and low temperature air. A plurality of air introduction holes 832 are formed on the outer periphery of the middle portion of the burner liner 83, through which the high temperature air is introduced into the burner liner 83 as secondary air. Further, a plurality of other air introduction holes 833 are formed on the outer periphery of the end portion of the burner liner 83, through which the high temperature air is introduced as dilution air.

As described above, the transient duct 23 and the burner liner 83 are each independently supported in a cantilever manner, and a clearance is formed at the connecting portion between the two. That is, a step 834 is formed at the outlet end of the burner liner 83, and the step 834 fits loosely into the inlet end of the transient duct 23. This allows transient duct 2
Even if the burner liner 3 and the burner liner 83 thermally expand in the longitudinal direction, the connection portions thereof are prevented from coming into contact and generating thermal stress. As is clear from FIG. 16, the radial clearance δ1 of the connection portion is formed smaller than the axial clearance δ2, and although the axial clearance δ2 changes greatly due to thermal expansion, the radial clearance δ1 doesn't change much. The amount of high-temperature air introduced from the joint into the transient duct 23 is determined by the relatively small radial gap δ1, and since the gap δ1 does not change significantly as described above, the high temperature air introduced from the connection The amount of air is kept approximately constant regardless of temperature. As a result, it is possible to always introduce a constant amount of high-temperature air into the transient duct 23 via the stepped portion 834, and it is possible to prevent fluctuations in the air-fuel ratio.

[0046] The igniter 84 is attached to the outer casing 1.
A bolt 94 is inserted through a fixing member 93 to the boss 12 formed in the
It is fixed in place and can be easily attached and detached from the outside. A guide member 95 is welded to the opening 182 of the inner casing 18 through which the igniter 84 passes, and a slider 97 provided on a cylindrical support member 96 through which the igniter 84 is inserted is slidably supported on the guide member 95. be done. A cooling air passage 98 is formed between the support member 96 and the igniter 84, and a seal member 99 is attached to the tip thereof. As a result, even if each part is displaced due to thermal expansion and vibration occurs at the tip of the igniter 84, the vibration is absorbed by the slider 97 provided on the support member 96 of the igniter 84 sliding against the guide member 95. Ru. The low temperature air flowing through the air passage 19 between the outer casing 1 and the inner casing 18 is introduced into the cooling air passage 98 inside the support member 96, and efficiently cools the igniter 84.

FIG. 17 shows a modification of the cooling structure of the igniter 84. In this modification, a ceramic shutoff member 100 slidably attached to the tip of the support member 96 is biased by a spring 101 to cool the burner. liner 83
touches the outer periphery of the This covers the igniter 84 and prevents hot air from coming into direct contact with the igniter 84.

Next, the operation of the embodiment of the present invention having the above-described configuration will be explained.

The air that has passed through the air cleaner 4 and the silencer 5 and entered the intake passage 6 is compressed to a high pressure of about 200°C by the compressor rotor 17 disposed inside the compressor casing 15, and the air is compressed to approximately 200°C, and the air is compressed to approximately 200°C. The air is sent rearward through radial air passages 19 formed between the air passages 18 and 18. The air passage 19
The high-pressure air that has reached the inside of the exhaust housing 3 gathers in the upper space of the exhaust housing 3, then changes its direction forward and passes over the upper half of the core surface of the rotary heat exchanger 13 from back to front. pass. The air passed through the heat exchanger 13 and heated to about 800° C. flows into the inner space of the inner casing 18 through the opening 291 formed in the upper part of the collector housing 29.

A part of the high temperature air supplied to the internal space of the inner casing 18 is sucked in as primary air through three openings 92 formed between the burner liner 83 and the liner support member 86, and passes through the swirler 91. As a result, it becomes a vortex and reaches the inside of the burner liner 83. The primary air flows from the air inlet 832 to the burner liner 83.
Along with the secondary air flowing into the interior of the fuel injection nozzle 82
It mixes with the fuel injected from the fuel and burns it. The combustion gas is mixed with dilution air introduced from the air introduction hole 833 and supplied to the scroll 24 via the transient duct 23, from where it passes between six nozzle vanes 25 and nozzles 32 and is blown onto the high-pressure turbine rotor 20. .

When the high-pressure turbine rotor 20 rotates in this manner, the compressor rotor 17 provided on the high-pressure turbine shaft 16 rotates due to its driving force. The combustion gas that has passed through the high-pressure turbine rotor 20 is blown onto the low-pressure turbine rotor 31 via the low-pressure turbine duct 34 and the variable stator blades 33, and rotationally drives the low-pressure turbine shaft 30. The rotation of the low-pressure turbine shaft 30 is then reduced by the reducer 14 and taken out from the output shaft 35. The exhaust gas that has passed through the low-pressure turbine rotor 31 is collected by an exhaust gas passage 292 formed at the bottom of the collector housing 29, and then passes through the lower half of the core surface of the rotary heat exchanger 13 from front to back. The heat exchanger 13 is heated and the heat is discharged to the exhaust duct 8. The heat exchanger 13 heated by the exhaust gas in this way is driven by the heat exchanger drive motor 40.
The heated core surface sequentially faces the intake air passage and heats the intake air.

[0052] As the gas turbine engine G operates, the members that come into contact with the combustion gas are exposed to high temperatures, so thermal expansion occurs due to the temperature rise. For example, the scroll 24 thermally expands mainly in the circumferential direction;
Since the pieces are divided into pieces 41 to 44 and butted together at the joints, even if the expansion amount of each piece 41 to 44 is uneven, excessive stress is prevented from being generated due to relative displacement of the joints. be done. Further, the thermal expansion of the scroll 24 in the radial direction is caused by the support mechanism 26 supporting the outer periphery of the scroll 24.
This prevents excessive stress from occurring.

The transient duct 23 disposed between the combustor 12 and the scroll 24 is also exposed to high temperatures;
and is supported by support mechanisms 27 and 28 from the outer casing 1,
It is held in a non-contact state with the burner liner 83. Therefore, not only is thermal stress prevented from occurring between the burner liner 83 but also the transient duct 2
3 and the outer casing 1 can be absorbed by the support mechanisms 27 and 28.

On the other hand, the back plate 21 and the high pressure turbine shroud 2 are in contact with the combustion gas from the scroll 24.
2. The nozzle vane 25 also undergoes relative displacement due to thermal expansion. However, these scrolls 24, back plate 2
1. The high-pressure turbine shroud 22 and the nozzle vane 25 are formed separately and overlapped in the axial direction, and are held together by being pressed by the pressing member 75 urged by the elastic force of the spring 74. The displacement is absorbed at the joint, and thermal stress is prevented from occurring.

Next, a second embodiment of the present invention will be described with reference to FIGS.
The explanation will be based on 1. FIG. 18 is a cross-sectional view of a gas turbine engine corresponding to FIG. 2, and FIG.
20 is a sectional view taken along line 20-20 in FIG. 19, and FIG. 21 is a sectional view taken along line 21-21 in FIG.

In this embodiment, each of the four pieces 41 to 44 constituting the scroll 24 has a bulge 243 at the outlet end.
is formed, and this bulge 243 is attached to the next pieces 41~
The shape of the scroll 24 is maintained by connecting it to the inlet end of the scroll 24 with a spigot. As is clear from Figure 20,
There is a slight gap δ in the circumferential direction at the joint of each piece 41 to 44.
3 is formed, and the pieces 41 to 44 are prevented from coming into close contact with each other due to thermal expansion and generating excessive stress.

Instead of holding the scroll 24 from the outer circumference by the support mechanism 26 adopted in the previous embodiment, the scroll 24 is held from the inner circumference by the positioning mechanism 102.
is maintained. That is, high pressure turbine shroud 2
A locking flange 244 is integrally provided on the inner periphery of each piece 41 to 44 that abuts on the outer periphery of the high pressure turbine shroud and projects radially inward. 22 is pressed forward in the axial direction by a pressing member 75 urged by the spring 74 described above.

Two pins 71 passing through the front portions of two of the six nozzle vanes 25 are pins formed on the locking flanges 244 of the back plate 21 and the two pieces 42 and 44. It fits loosely into the hole 245 and is prevented from coming off by the seal ring 103 (see FIGS. 18 and 21). At this time, the four pieces 41 to 44 are joined together by the bulge 243 and the shape is maintained as a whole, so that the scroll 24 is connected to the two pins 71.
It is held inside the inner casing 18 by a positioning mechanism 102 consisting of a and a locking flange 244. Note 6
Six pins 7 locked at the rear of the nozzle vanes 25
2 penetrates the high-pressure turbine shroud 22 and engages with six pressing members 75 at corresponding positions, thereby positioning the nozzle vane 25 and the pressing members 75.

On the other hand, the back plate 21 is supported with respect to the base plate 58 by inserting the retainer 1 into the roller groove 1041 of the roller support member 104 provided on the base plate 58.
This is done by engaging the roller 60, which is locked at 05, into the roller groove 211 of the back plate 21. As in the previous embodiment, the rollers 60 are arranged radially in three rows at intervals of 120°.
As a result, displacement due to thermal expansion of the base plate 58 and the back plate 21 is absorbed, and concentricity of both is achieved.

Four pieces 41 to 44 of scroll 24
A seal ring 107, which is biased by a spring 106 provided on the base plate 58 side, comes into contact with each joint of the base plate 58.
The seal ring 1 is biased by a spring 108 which is also provided on the base plate 58 side in the radial direction.
09 comes into contact with the back plate 21. As a result, the scroll 24, the back plate 21, the nozzle vane 25,
The high-pressure turbine shroud 22 is given elastic force by the springs 106, 108, and 74 from the front and rear in the axial direction, and is held together in a state that can compensate for the difference in thermal expansion.

The partition member 110 disposed between the compressor rotor 17 and the high-pressure turbine rotor 20 has a labyrinth 1101 at the contact portion with the high-pressure turbine shaft 16, and is introduced into the air chamber 111 from the outlet end of the compressor rotor 17. The cold air cools the high pressure turbine shaft 16 as it passes through the labyrinth 1101 .

FIG. 22 shows a third embodiment of the present invention, in which the four pieces 4 of the scroll 24 are
1 to 44 are jointed in a spigot joint with a clearance between them through the bulge 243 as in the second embodiment. An annular groove 246 is formed in the inner periphery of the scroll 24 facing the outer periphery of the high-pressure turbine shroud 22, and an annular projection 223 that engages with the annular groove 246 is provided in a protruding manner on the outer periphery of the high-pressure turbine shroud 22. The pressing member 75 urged by the spring 74 contacts only the high-pressure turbine shroud 22, and its pressing force is applied to the annular protrusion 223 and the annular groove 246 from the high-pressure turbine shroud 22.
to the scroll 24 to hold the scroll 24 in place. In this embodiment, the annular groove 246 and the annular protrusion 223 constitute the positioning mechanism 102 for the scroll 24.

The nozzle vane 25 has a pin 71 that engages the high pressure turbine shroud 22 and the pressing member 75 at its front portion.
The rear portion thereof is locked by a pin 72 that engages with the back plate 21. Also, as in the second embodiment, the back plate 21 is attached to the base plate 58 by three.
The back plate 21 is supported via the rollers 60 of
The outer periphery of the scroll 24 and the inner periphery of the scroll 24 are each provided with a spring 106.
, 108 are supported by seal rings 107, 109.

The base plate 58 has an air passage 1 formed between the outer casing 1 and the inner casing 18.
An air passage 582 communicating with the labyrinth 5 is formed, and the low temperature air introduced from the air passage 19, 582 is
84, the high pressure turbine shaft 16 is cooled.

23 to 25 show a fourth embodiment of the present invention. FIG. 23 is a cross-sectional view of a gas turbine engine corresponding to FIG. 10, and FIG. 24 is a cross-sectional view taken along the line 24--24 in FIG. , FIG. 25 is a sectional view taken along the line 25-25 in FIG. 23.

The scroll 24 of this embodiment has four coupling flanges 247 at the outlet end of each piece 41-44.
is provided in a protruding manner, and the four pieces 41 to 44 are joined to each other at this connecting flange 247, thereby forming the scroll 24.
The overall shape of is maintained. The pressing member 112, which is biased by the elastic force of the plurality of springs 74, is made of a single annular member, and has four hemispherical pressing parts 1121 protruding from its inner periphery.
The high pressure turbine shroud 22 is pressed by the high pressure turbine shroud 22.

Locking protrusions 249 that come into contact with each other are provided on the inner periphery of the joints of the respective pieces 41 to 44 of the scroll 24 and protrude backward, and four pressing parts 1122 are protruded on the outer periphery of the pressing member 112. will be established. Pressing member 11
The pressing portion 1122 of No. 2 is formed into two forks, and this pressing portion 1
122 , the two locking protrusions 249 of the adjacent pieces 41 to 44 are sandwiched and pressed forward. As a result, the outer periphery of the high-pressure turbine shroud 22 and the scroll 2
The sealing surfaces 224 and 248 formed on the inner peripheries of 4 are in close contact with each other. At this time, since the contact surfaces between the pressing portion 1122 and the locking protrusion 249 are formed to be inclined in a V-shape (see FIG. 25), the pieces 41 to 44 are pressed against each other to maintain their shape. Thus, the scroll 24 and the high-pressure turbine shroud 22 are simultaneously pressed by the inner and outer pressing parts 1121 and 1122 of the annular pressing member 112, and the pressing force causes the high-pressure turbine shroud 22,
Scroll 24, back plate 21, and nozzle vane 25 are held together.

FIGS. 26 and 27 show a fifth embodiment of the present invention. As in the previous fourth embodiment, the pieces 41-44 of the scroll 24 in this embodiment are joined together by a joining flange 247.

Locking protrusions 2410 that come into contact with each other are provided on the inner periphery of the joints of the pieces 41 to 44 of the scroll 24 to protrude forward. On the other hand, 4 formed on the base plate 58
The sliding members 113 are fitted into each of the recesses 585 so as to be movable in the axial direction, and each is biased backward by two springs 114. In the recess 1131 formed on the rear surface of the sliding member 113,
Two gripping claws 115 are arranged in a V-shape so as to sandwich the locking protrusions 2410 of adjacent pieces 41 and 44, and their opposing parts are biased in the direction of mutual expansion by leaf springs 116. . Both gripping claws 115 are urged in the closing direction by the elastic force of the pressing member 75 from the rear and the elastic force of the sliding member 113 from the front, and hold each piece 41 to 44 of the scroll 24 together. At the same time, it is positioned relative to the base plate 58.

FIGS. 28 and 29 show a sixth embodiment of the present invention. The four pieces 41 to 44 of the scroll 24 in this embodiment are mutually spigot-coupled by a bulge 243, but unlike the second embodiment shown in FIG.
The spigot joint is tightly joined without any clearance.

Scroll 24 integrated in this way
is held by four support mechanisms 117 from the outer periphery. That is, a support rod 120 having a quadrant-shaped cross section is fixed to a base plate 119 supported by a boss 13 protruding from the outer casing 1 via a leaf spring 118 so as to protrude rearward. The support rod 120 has each piece 41 to 44.
The elastic force of the leaf spring 118 presses the scroll 24 inward in the radial direction to position and fix the scroll 24. According to this embodiment, the scroll 24 is held by applying a radially inward pressing force from the outer casing 1 as in the first embodiment.

30 to 32 show a seventh embodiment of the present invention. FIG. 30 is a cross-sectional view of a gas turbine engine corresponding to FIG. 2, and FIG. 31 is an enlarged view of part 31 of FIG. 32 is a sectional view taken along line 32-32 in FIG.

The four pieces 41 to 44 of the scroll 24 of this embodiment are joined by abutting, and three joining protrusions 2411 are protruded from the joint part at 120° intervals so as to face each other. Ru. Opposing coupling protrusions 241
A pin 121 passes through the pin 121, and a fixed clamp member 122 provided at the end of the pin 121 and a movable clamp member 124 that is slidably supported by the pin 121 and biased by a spring 123 are connected to each other. The projection 2411 is pressed in the circumferential direction of the scroll 24. As a result, the four pieces 41 to 44 are joined together, and the outer shape of the scroll 24 is maintained.

33 and 34 show an eighth embodiment of the present invention, and FIG. 33 is a diagram corresponding to FIG. 31, and FIG.
4 is a sectional view taken along the line 34-34 in FIG. 33.

[0075] This embodiment also has the same features as the seventh embodiment described above.
Each piece 41 to 44 of the scroll 24 is fixed together by elastic force in the circumferential direction. That is, three coupling protrusions 2411 each having a small protrusion height are protruded from the four pieces 41 to 44 joined by abutting so as to face each other. This coupling projection 2411 is held between a C-shaped fixed clamp member 125 and a movable clamp member 126, and is clamped by the elastic force of a spring 123 attached to three pins 121 that pass through both clamp members 125 and 126. .

FIG. 35 shows a ninth embodiment of the present invention, and corresponds to FIG. 31 described above.

[0077] This example is a combination of 4
Three coupling protrusions 2411 formed on each of the pieces 41 to 44 so as to face each other are secured by heat-resistant fibers 127, and thereby each piece 41, 44 is given a pressing force in the circumferential direction. be integrated.

Although the embodiments of the present invention have been described in detail above, the present invention is not limited to the above embodiments, and various modifications may be made without departing from the scope of the present invention described in the claims. Design changes are possible.

[0079]

As described above, according to the first feature of the present invention, the scroll, the back plate, the nozzle vane, and the shroud are each formed separately, and the scroll, the back plate, the nozzle vane, and the shroud are each formed separately, and they are pressed together by a pressing member having at least two or more pressing portions. Since the nozzle vane is positioned and fixed as a width determining member, appropriate pressure is applied to the scroll disposed on the outside in the radial direction, and the back plate, nozzle vane, and shroud disposed on the inside thereof. By applying elastic force, they can be reliably positioned and fixed. Furthermore, since the nozzle vane is used as a width determining member, the back plate and shroud can be maintained at a predetermined distance. In addition, since the shape of each member is smaller and simpler than when these parts are formed as one piece, it is not only advantageous against thermal stress, but also facilitates manufacturing and improves product yield. will improve. Furthermore, since each member is relatively movable, it is possible to absorb the difference in the amount of thermal expansion and prevent generation of excessive stress.

According to the second feature of the present invention, the nozzle vane is pinched from the front and back by the back plate and the shroud, and one of the positioning members protruding from the front and rear of the nozzle vane is locked to the back plate and the other to the shroud. Therefore, the back plate and the shroud can be relatively movably connected using the nozzle vane as an intermediary.

According to the third feature of the present invention, since the pressing member applies a pressing force to at least the scroll and the shroud, the shroud is capable of applying a large pressing force, and the shroud is capable of applying only a small pressing force. Appropriate pressing force can be distributed to the scrolls that cannot be moved. Also, the different thermal expansions of the backplate and shroud can be accommodated by the displacement of the nozzle vanes.

According to the fourth feature of the present invention, the pressing member is provided with two or more pressing portions spaced apart in the radial direction, so that a common pressing member applies pressing force to both the scroll and the shroud. The number of parts can be reduced.

According to the fifth feature of the present invention, the pressing member is divided into a plurality of members disposed in the circumferential direction and in contact with each other, so that thermal expansion of the scroll and the shroud is prevented in the circumferential direction. Even if they are non-uniform, a uniform pressing force can be applied to them. Furthermore, each pressing member can be automatically positioned by mutual contact.

According to the sixth feature of the present invention, at least one of the plurality of divided pressing members is locked to the shroud by the positioning member, so that the positioning of each pressing member can be made more reliable. Become.

According to the seventh feature of the present invention, the scroll is divided into a plurality of sections by cross sections intersecting the combustion gas passage, which reduces thermal stress and manufacturing costs compared to the case where the entire scroll is formed in one piece. Not only is it advantageous in terms of
The difference in thermal expansion can be absorbed at the joint.

According to the eighth feature of the present invention, the back plate is supported by the casing with a positioning key interposed, so that the scrolls, nozzle vanes, and shrouds stacked on the back plate can be placed at predetermined positions within the casing. can be retained. Further, the interposition of the key member prevents heat transfer from the high temperature back plate to the housing, thereby improving heat insulation.

According to a ninth feature of the present invention, the positioning means is composed of mutually opposing guide grooves formed in the radial direction on the casing side and the back plate, respectively, and a rotary key that engages with these guide grooves. Therefore, the difference in the amount of thermal expansion in the radial direction between the casing and the back plate can be absorbed with a small frictional force, and the back plate can be centered with respect to the casing.

According to the tenth feature of the present invention, since the back plate is divided into a radially outer portion and a radially inner portion, distortion due to a temperature difference between the two portions of the back plate can be absorbed.

According to the eleventh feature of the present invention, a sealing member is interposed between the radially outer portion and the radially inner portion of the back plate, thereby preventing air from flowing from the connecting portion of both portions of the back plate. Leakage can be prevented.

[Brief explanation of drawings]

[Figure 1] Longitudinal cross-sectional view of a gas turbine engine

[Figure 2] Figure 1
2-2 line sectional view of

[Figure 3] Enlarged view of main parts of Figure 2

[Figure 4] Enlarged view of part 4 of Figure 3

[Figure 5] Enlarged view of part 5 of Figure 3

[Figure 6] Enlarged view of main parts of Figure 2

[Figure 7] Enlarged view of main parts of Figure 2

[Figure 8] Cross-sectional view taken along line 8-8 in Figure 7

[Figure 9] Enlarged view of main parts of Figure 1

[Fig. 10] View from line 10-10 in Fig. 1

[Figure 11] Cross-sectional view taken along line 11-11 in Figure 10

[Figure 12] Figure 2
Enlarged view of main parts

[Figure 13] Enlarged view of main parts in Figure 12

[Figure 14] Cross-sectional view taken along line 14-14 in Figure 13

[Figure 15] Figure 1
Explanatory diagram of the action corresponding to 4

[Figure 16] Enlarged view of section 16 in Figure 12

[Fig. 17] A diagram showing a modification of the igniter mounting part.

[Figure 18
]A cross-sectional view of a gas turbine engine according to a second embodiment of the present invention.

[Figure 19] Cross-sectional view taken along line 19-19 in Figure 18

[Figure 20] Figure 1
9 20-20 line sectional view

[Figure 21] 21-21 in Figure 18
Line cross section

FIG. 22 is an enlarged view of the main parts of a gas turbine engine according to a third embodiment of the present invention.

FIG. 23 is a cross-sectional view of a gas turbine engine according to a fourth embodiment of the present invention.

[Fig. 24] Cross-sectional view taken along line 24-24 in Fig. 23

[Figure 25] Figure 2
25-25 line sectional view of 3

FIG. 26 is an enlarged view of the main parts of a gas turbine engine according to a fifth embodiment of the present invention.

[Fig. 27] Cross-sectional view taken along line 27-27 in Fig. 26

FIG. 28 is a cross-sectional view of a gas turbine engine according to a sixth embodiment of the present invention.

[Fig. 29] Cross-sectional view taken along line 29-29 in Fig. 28

FIG. 30 is a cross-sectional view of a gas turbine engine according to a seventh embodiment of the present invention.

[Figure 31] Enlarged view of part 31 in Figure 30

[Figure 32] Cross-sectional view taken along line 32-32 in Figure 31

FIG. 33 is a diagram showing a joint part of a scroll according to an eighth embodiment of the present invention.

[Figure 34] Cross-sectional view taken along line 34-34 in Figure 33

FIG. 35 is a diagram showing a joint part of a scroll according to a ninth embodiment of the present invention.

[Explanation of symbols]

1... Outer casing (casing) 21...
Back plate 22...High pressure turbine shroud (shroud) 24
... Scroll 25 ... Nozzle vane 581 ... Roller groove (guide groove) 60 ... Roller (rotation key) 61 ... Back plate outer (outer part) 611
...Roller groove (guide groove) 62...Back plate inner (inner part) 68...
- Seal ring (sealing member) 71... Pin (positioning member) 72... Pin (positioning member) 75... Pressing member 751... Pressing protrusion (pressing part) 752... Pressing protrusion (pressing part) 112・Press member 1121 ・Press projection (press portion) 1122 ・Press projection (press portion)

Claims (11)

[Claims] [Claim 1] A back plate (21), a nozzle vane (25) and a shroud (2) are provided inside the casing (1).
2) are overlapped in the axial direction, and a scroll (24) is disposed on the outer periphery of the two, in which the scroll (24), the back plate (21), the nozzle vane (5), and the shroud (22) are each separated. and at least two or more pressing parts (751, 7
52 ; 1121 , 1122 ) having a pressing member (
75, 112) elastically biased in the axial direction, and the nozzle vane (25) is positioned and fixed as a width determining member. 2. The nozzle vane (25) is pinched from the front and back by the back plate (21) and the shroud (22), and one of the positioning members (71, 72) protruding from the front and rear of the nozzle vane (25) is placed between the back plate (21) and the shroud (22). 2
2. A gas turbine engine according to claim 1, characterized in that in the first part, the other part is fixed to the shroud (22). 3. The gas turbine engine according to claim 1, wherein a pressing force is applied to at least the scroll (24) and the shroud (22) by a pressing member (75, 112). 4. The pressing member (75, 112) has two or more pressing parts (751, 752) spaced apart in the radial direction.
; 1121 , 1122 ). The gas turbine engine according to claim 3 . 5. The gas turbine engine according to claim 3, wherein the pressing member (75) is divided into a plurality of members arranged in a circumferential direction and in contact with each other. 6. The pressing member (75
Gas turbine engine according to claim 5, characterized in that at least one of the shrouds (22) is locked by a positioning member (71). 7. The gas turbine engine according to claim 1, wherein the scroll (22) is divided into a plurality of sections by a cross section intersecting a combustion gas passage. 8. The gas turbine engine according to claim 1, wherein the back plate (21) is supported by the casing (1) with a positioning key interposed therebetween. 9. The positioning means includes a casing (1
) side and the back plate (21), mutually opposing guide grooves (581, 611) formed in the radial direction, respectively.
9. The gas turbine engine according to claim 8, further comprising: and a rotary key (60) that engages with these guide grooves. 10. Gas turbine engine according to claim 1, characterized in that the back plate (21) is divided into a radially outer part (61) and a radially inner part (62). 11. The gas according to claim 10, characterized in that a sealing member (68) is interposed between the radially outer portion (61) and the radially inner portion (62) of the back plate (21). turbine engine.