Gas turbine

Abstract

Provided is a gas turbine comprising a partitioning portion (81) that partitions an upstream-side space of a turbine disk into a first space (US1) to which compressed air (PA) is supplied and a second space (US2) in which the turbine disk is disposed, and a nozzle portion (90) that is formed in a tubular shape so as to guide the compressed air (PA) from an inflow port (91) opening into the first space (US1) toward an outflow port (92) opening into the second space (US2), wherein an outflow surface (OS) in which the outflow port (92) is disposed is disposed so as to be parallel to a first direction (DR1) along an axis (X) or so as to intersect the first direction (DR1) at an angle of 10 degrees or less, and is disposed so as to be perpendicular to a second direction along the tangent of a virtual circle passing through the nozzle portion (90) with the axis (X) as the center, or so as to be inclined at an angle of 45 degrees or less toward the inner peripheral side in the radial direction connecting the axis (X) and the nozzle portion (90) with respect to the second direction.

Description

Gas Turbine

[0001] The present disclosure relates to a gas turbine.

[0002] Conventionally, gas turbines used as aircraft engines are known (see, for example, Patent Document 1 and Patent Document 2). The gas turbine disclosed in Patent Document 1 includes a high-pressure turbine that drives a compressor and a low-pressure turbine that drives a fan. In Patent Document 1, compressed air compressed by the compressor is guided through an orifice into a space inside a disc to which moving blades are attached, for cooling high-temperature portions of the gas turbine.

[0003] Further, Patent Document 2 discloses that in order to guide cooling air to a cooling passage hole formed in a rotor to which moving blades are attached, cooling air having both an axial velocity component and a circumferential velocity component of the rotor is blown out from a tubular nozzle. The cooling air blown out from the tubular nozzle, which is disposed upstream of the cooling passage hole in the flow direction of combustion gas, is guided to the cooling passage hole while moving in the flow direction of the combustion gas, and cools the rotor when passing through the cooling passage hole.

[0004] US Patent Application Publication No. 2024 / 0151151 Japanese Unexamined Patent Application Publication No. 2007-298020

[0005] However, both the compressed air blown out from the orifice of Patent Document 1 and the cooling air blown out from the tubular nozzle of Patent Document 2 have a high proportion of velocity components along the flow direction of combustion gas. Therefore, compared to the velocity component along the flow direction of combustion gas, the circumferential velocity component corresponding to the rotation of the disc and the rotor is relatively smaller in the compressed air blown out from the orifice and the cooling air blown out from the tubular nozzle. As a result, while the cooling effect for rotating bodies such as the disc and the rotor is high, the effect of applying torque to the disc and the rotor is reduced.

[0006] The present disclosure has been made in view of such circumstances, and an object thereof is to provide a gas turbine capable of improving turbine performance by applying sufficient torque to a turbine disk to which a plurality of moving blades are connected while cooling the turbine disk.

[0007] To solve the above problems, a gas turbine according to one aspect of the present disclosure includes a compressor having a plurality of compression blades that rotate around an axis and compressing external air to generate compressed air, a combustor that burns the compressed air generated by the compressor together with fuel to generate combustion gas, a turbine disk having a plurality of blades that rotate around an axis and a turbine disk to which the blades are connected, and which is driven by the combustion gas generated by the combustor, a rotating shaft that connects the compressor and the turbine disk and is formed to extend along the axis and rotates in the rotational direction, and the upstream space of the turbine disk in the flow direction of the combustion gas is arranged between a first space to which the compressed air is supplied and the turbine disk. The device comprises a partition portion that divides the space into a second space, and nozzle portions that are arranged at multiple locations in the circumferential direction around the rotation axis of the partition portion and are formed in a tubular shape to guide the compressed air from an inlet opening to the first space to an outlet opening to the second space, wherein the outlet surface of the nozzle portion is arranged to be parallel to a first direction along the axis, or to intersect the first direction at an angle of 10 degrees or less, and to be perpendicular to a second direction along the tangent to a virtual circle passing through the nozzle portion with the axis as the center, or to be inclined at an angle of 45 degrees or less toward the inner circumference in the radial direction connecting the axis and the nozzle portion with respect to the second direction.

[0008] According to this disclosure, it is possible to provide a gas turbine capable of improving turbine performance by cooling the turbine disk, to which multiple rotor blades are connected, while simultaneously applying sufficient torque to the turbine disk.

[0009] This is a longitudinal cross-sectional view showing a gas turbine according to one embodiment of the present disclosure. This is a partially enlarged view of portion A of the gas turbine shown in Figure 1. This is a view of the partition and nozzle shown in Figure 2 from the downstream side in the direction of combustion gas flow. This is a view of the partition shown in Figure 2 from the upstream side in the direction of combustion gas flow. This is a cross-sectional view of the nozzle shown in Figure 2 taken along the line B-B. This is an enlarged view of the nozzle shown in Figure 2. This is a cross-sectional view of the nozzle of the first modified example taken along the line B-B. This is a view of the partition and nozzle of the second modified example taken from the downstream side in the direction of combustion gas flow.

[0010] Hereinafter, a gas turbine 100 according to one embodiment of the present disclosure will be described with reference to the drawings. Figure 1 is a longitudinal cross-sectional view showing a gas turbine 100 according to one embodiment of the present disclosure. Figure 2 is a partially enlarged view of portion A of the gas turbine 100 shown in Figure 1. The gas turbine 100 of this embodiment is used, for example, as a thrust generating device for an aircraft.

[0011] As shown in Figures 1 and 2, the gas turbine 100 comprises a compressor 10, a combustor 20, a turbine 30, a supercharger fan 40, an inner casing 50, an outer casing 60, a rotating shaft 70, a structure 80, and a nozzle section 90.

[0012] The compressor 10 is a device that generates compressed air by compressing external air EA flowing in from the front of the aircraft's direction of travel. The compressor 10 has a plurality of rotor blades (compression rotor blades) 11 that rotate around axis X and are connected to a rotating shaft 70, and generates compressed air by passing the incoming external air EA through the plurality of rotor blades 11.

[0013] The combustor 20 is a device that burns compressed air generated by the compressor 10 together with fuel to produce high-temperature, high-pressure combustion gas CA. The combustor 20 supplies the high-temperature, high-pressure combustion gas CA to the turbine 30, thereby rotating the turbine 30 around axis X. Multiple combustors 20 are installed around axis X.

[0014] The turbine 30 is a device driven by the combustion gas CA generated by the combustor 20. The turbine 30 includes a high-pressure turbine 31, a low-pressure turbine 32 positioned downstream of the high-pressure turbine 31 in the flow direction of the combustion gas CA, and a plurality of stationary blades 33 positioned between the high-pressure turbine 31 and the low-pressure turbine 32 and connected to the inner casing 50. The high-pressure turbine 31 has a plurality of high-pressure turbine blades 31a connected to the rotating shaft 70. The low-pressure turbine 32 has a plurality of low-pressure turbine blades 32a connected to the rotating shaft 70.

[0015] The low-pressure turbine 32 has a plurality of low-pressure turbine blades 32a that rotate around an axis X, and a turbine disk 32b connected to the low-pressure turbine blades 32a. The low-pressure turbine blades 32a have a blade portion 32a1 and a platform portion 32a2 formed integrally with the blade portion 32a1. The blade portion 32a1 is connected to the turbine disk 32b, which is mounted on the rotating shaft 70, via the platform portion 32a2.

[0016] By introducing combustion gas CA to the turbine 30, multiple high-pressure turbine blades 31a and multiple low-pressure turbine blades 32a are driven to rotate around axis X. The driving force that causes the high-pressure turbine blades 31a and low-pressure turbine blades 32a to rotate around axis X is transmitted to the compressor 10 via the rotating shaft 70. The compressor 10 generates compressed air by rotating the blades 11 using the power obtained from the turbine 30.

[0017] The supercharging fan 40 is a device that rotates around axis X to supply external air EA to both the internal space of the inner casing 50 and the space between the inner casing 50 and the outer casing 60. The supercharging fan 40 is connected to the turbine 30 via a rotating shaft 70. The supercharging fan 40 rotates around axis X when driven by the turbine 30 and guides the external air EA to the compressor 10.

[0018] The inner casing 50 is formed in a cylindrical shape extending along the axis X and is positioned outside the turbine 30 with respect to the axis X. The inner casing 50 includes a turbine casing 51 positioned on the outer circumference of the turbine 30 and an exhaust casing 52 connected to the turbine casing 51 on the downstream side in the flow direction of the combustion gas CA. The outer casing 60 is formed in a cylindrical shape extending along the axis X and is positioned outside the inner casing 50 with respect to the axis X.

[0019] The rotating shaft 70 is a shaft-shaped member that connects the compressor 10 and the turbine 30 and extends along the axis X, and rotates in the rotational direction RD (see Figures 3 and 4). The turbine disk 32b of the low-pressure turbine 32 is connected to the compressor 10 by the rotating shaft 70.

[0020] The structure 80 is a member connected to the inner casing 50 via the stationary vanes 33. The structure 80 is positioned adjacent to the upstream side in the flow direction of the combustion gas CA, above the low-pressure turbine 32, which is located at the uppermost upstream side in the flow direction of the combustion gas CA. As shown in Figure 2, the structure 80 has a partition portion 81 and a bulkhead portion 82.

[0021] The partition 81 is a circular member in plan view that divides the upstream space US in the flow direction of the combustion gas CA of the turbine disk 32b into a first space US1 to which compressed air PA is supplied and a second space US2 to which the turbine disk 32b is located. The partition 81 is positioned perpendicular to the axis X of the rotation shaft 70. A through hole 81a is formed in the center of the partition 81 through which the rotation shaft 70 passes.

[0022] A seal arm 81b is formed in the partition portion 81, which is annular in shape around the axis X and protrudes toward the turbine disk 32b. On the outer circumference side of the seal arm 81b with respect to the axis X, a seal arm 32b1 is formed, which is annular in shape around the axis X and protrudes from the turbine disk 32b toward the partition portion 81. The seal arm 81b and the seal arm 32b1 are arranged so as to have overlapping regions in the direction along the axis X. The seal arm 81b and the seal arm 32b1 form a seal structure that prevents the high-temperature combustion gas CA flowing outside the partition portion 82 with respect to the axis X from being guided into the second space US2.

[0023] The partition wall portion 82 is formed in a cylindrical shape extending along the axis X and is a member arranged inside the inner casing 50 so as to form a first space US1 together with the partition portion 81. The partition wall portion 82 is formed integrally with the partition portion 81, but it may also be arranged separately from the partition portion 81. Stator vanes 33, which are arranged at multiple locations in the circumferential direction around the axis X, connect the inner casing 50 and the partition wall portion 82.

[0024] As shown in Figure 2, a compressed air passage 33a is formed inside the stationary vane 33 to guide compressed air from the outside of the inner casing 50 to the first space US1 inside the partition wall 82. The compressed air PA generated by the compressor 10 is guided to the area outside the inner casing 50 via a compressed air passage (not shown) connecting the compressor 10 and the area outside the inner casing 50, and is supplied to the first space US1 via the compressed air passage 33a.

[0025] Next, the nozzle section 90 located in the partition section 81 will be described with reference to the drawings. Figure 3 is a view of the partition section 81 and nozzle section 90 shown in Figure 2, seen from the downstream side in the flow direction of the combustion gas CA. Figure 4 is a view of the partition section 81 shown in Figure 2, seen from the upstream side in the flow direction of the combustion gas CA. Figure 5 is a cross-sectional view of the nozzle section 90 shown in Figure 2, taken along the line B-B. Figure 6 is an enlarged view of the nozzle section 90 shown in Figure 2. Figure 2 is a cross-sectional view taken along the line C-X-C in Figure 3.

[0026] As shown in Figure 3, the nozzle sections 90 are arranged at five locations along the circumferential direction CD around the rotation axis 70 of the partition section 81, at equal intervals of 72 degrees. Each nozzle section 90 is positioned at an equidistant distance from the axis X. In the example shown in Figure 3, the nozzle sections 90 are arranged at five locations along the circumferential direction CD with 72-degree intervals, but any number of nozzle sections 90 may be arranged at equal intervals along the circumferential direction CD.

[0027] As shown in Figures 2 to 4, the nozzle section 90 has an inlet 91 that opens into the first space US1. As shown in Figures 2 and 3, the nozzle section 90 has an outlet 92 that opens into the second space US2. The nozzle section 90 is a tubular member formed to guide compressed air PA supplied to the first space US1 from the inlet 91 to the outlet 92. The nozzle section 90 is a type of nozzle called TOBI (Tangential On-board Injection), also known as a pre-swara.

[0028] As shown in Figures 3 and 5, the outlet 92 of the nozzle section 90 is positioned on an outlet surface OS parallel to the axis X. As shown in Figure 5, the outlet surface OS is a surface positioned parallel to the first direction DR1 along the axis X. Therefore, the compressed air PA blown out from the outlet 92 has no velocity component along the axis X, but only a velocity component along the circumferential direction CD.

[0029] Furthermore, as shown in Figure 3, the outlet surface OS is a surface positioned perpendicular to the second direction DR2 along the tangent TL of a virtual circle VC that passes through the center 91a of the inlet 91 of the nozzle section 90, with axis X as its center. Therefore, the compressed air PA blown out from the outlet 92 does not have a radial velocity component connecting axis X and the center 91a of the inlet 91 in a plane perpendicular to axis X, but only has a velocity component along the second direction DR2.

[0030] As shown in Figure 6, the outlet 92 of the nozzle section 90 is set such that the second length L2 along the radial direction RAD is longer than the first length L1 along the first direction DR1. The radial direction RAD is the direction along the straight line connecting the axis X and the center 91a of the inlet 91 of the nozzle section 90 in Figure 3. It is preferable to set the first length L1 in a range of 0.3 times or more and 0.8 times or less of the second length L2.

[0031] As shown in Figures 4 to 6, the nozzle section 90 is shaped such that the flow path cross-sectional area gradually decreases at each position from the inlet 91, which is circular in plan view, to the outlet 92, which is substantially elliptical in plan view. The nozzle section 90, in which the flow path cross-sectional area gradually decreases from the inlet 91 to the outlet 92, can gradually increase the flow velocity of the compressed air PA from the inlet 91 to the outlet 92 before blowing the compressed air PA towards the second space US2.

[0032] Furthermore, as shown in Figures 4 to 6, the flow path wall that defines the flow path of compressed air PA in the nozzle section 90 is formed of smoothly connected curved and flat surfaces. This reduces pressure loss when compressed air PA passes through the nozzle section 90.

[0033] [First Modified Example] In the above description, as shown in Figure 5, the outlet surface OS on which the outlet 92 of the nozzle portion 90 is located is arranged parallel to the first direction DR1 along the axis X, but other configurations are also possible. For example, the outlet surface OS may be arranged as shown in the first modified example in Figure 7. Figure 7 is a cross-sectional view of the nozzle portion 90A of the first modified example taken along the line B-B. The cross-sectional view taken along the line B-B in Figure 7 is obtained by replacing the nozzle portion 90 shown in Figure 2 with the nozzle portion 90A of the first modified example.

[0034] As shown in Figure 7, the outlet surface OS on which the outlet 92 of the nozzle section 90A of the first modified example is located is positioned to intersect the first direction DR1 along the axis X at an angle θ1. The angle θ1 is preferably 10 degrees or less, and particularly preferably 5 degrees or less. By setting the angle θ1 to 10 degrees or less, a sufficient circumferential velocity component of the compressed air PA blown out from the nozzle section 90A around the axis X can be secured, thereby forming a swirling flow around the axis X with the compressed air PA.

[0035] [Second Modification] In the above description, as shown in Figure 3, the outlet surface OS on which the outlet 92 of the nozzle section 90 is located is positioned perpendicular to the second direction DR2 along the tangent TL of a virtual circle VC that passes through the center 91a of the inlet 91 of the nozzle section 90 with axis X as its center. However, other configurations are also possible. For example, the outlet surface OS may be positioned as shown in the second modification shown in Figure 8. Figure 8 is a view of the partition section 81 and nozzle section 90B of the second modification as seen from the downstream side in the flow direction of the combustion gas CA.

[0036] As shown in Figure 8, the outlet surface OS on which the outlet 92 of the nozzle portion 90B of the second modified example is located is inclined at an angle θ2 toward the radial inner circumference with respect to the second direction DR2, connecting the axis X and the center 91a of the inlet 91 of the nozzle portion 90. The angle θ2 is preferably 15 degrees or more and 45 degrees or less.

[0037] By setting the angle θ2 to 45 degrees or less, sufficient circumferential velocity components around the axis X of the compressed air PA blown out from the nozzle section 90A can be secured, allowing the compressed air PA to form a swirling flow around the axis X. Furthermore, by setting the angle θ2 to 15 degrees or more, it is possible to suppress the compressed air PA blown out from the outlet 92 from being guided by centrifugal force toward the seal structure on the outer circumference of the nozzle section 90 relative to the axis X (a structure combining the seal arm 81b and the seal arm 32b1 shown in Figure 2). By suppressing the guidance of compressed air PA to the seal structure, it is possible to suppress the rise in temperature of the second space US2 by preventing the compressed air PA guided to the seal structure from generating strong vortices in the seal structure and drawing the combustion gas CA into the second space US2.

[0038] [Third Modification] In the above description, the outlet surface OS on which the outlet 92 of the nozzle portion 90 is located is positioned parallel to the first direction DR1 along the axis X, and perpendicular to the second direction DR2 along the tangent TL of a virtual circle VC that passes through the center 91a of the inlet 91 of the nozzle portion 90 with the axis X as its center. However, other embodiments are also possible.

[0039] For example, the nozzle section 90 may be configured to apply both the first and second modified examples described above. That is, the outlet surface OS may be positioned so as to intersect the first direction DR1 along the axis X at an angle θ1, and to be inclined at an angle θ2 toward the radial inner circumference side connecting the axis X and the center 91a of the inlet 91 of the nozzle section 90 with respect to the second direction DR2.

[0040] The operation and effects of the gas turbine 100 of this embodiment, as described above, will now be explained. According to the gas turbine 100 of this embodiment, the combustion gas CA generated in the combustor 20 imparts a torque to the low-pressure turbine blades 32a connected to the turbine disk 32b, causing the turbine disk 32b to rotate in the rotational direction RD. As the turbine disk 32b rotates, the compressor 10 connected via the rotating shaft 70 generates compressed air PA, which is supplied to the first space US1 in the upstream space US of the turbine disk 32b, separated by the partition 81. The compressed air PA supplied to the first space US1 flows into the inlet 91 of the nozzle 90 and is supplied from the outlet 92 to the second space US2 where the turbine disk 32b is located.

[0041] The outlet surface OS on which the nozzle outlet 92 of the nozzle section 90 is located is positioned parallel to the first direction DR1 along the axis X, or intersects the first direction DR1 at an angle θ1 of 10 degrees or less. The compressed air PA blown out from the nozzle section 90 has no velocity component along the flow direction of the combustion gas CA, or if it does, it is negligible. Furthermore, the outlet surface OS on which the nozzle outlet 92 of the nozzle section 90 is located is positioned perpendicular to the second direction DR2 along the tangent line TL of a virtual circle VC passing through the nozzle section 90 with axis X as the center, or is inclined at an angle θ2 of 45 degrees or less toward the inner circumference in the radial direction connecting axis X and the nozzle section 90 with respect to the second direction DR2.

[0042] Since the outflow surface OS is arranged as described above, the velocity component of the compressed air PA blown out from the nozzle portions 90 in the circumferential direction CD around the axis X becomes extremely large. A swirling flow that swirls in the circumferential direction CD is generated by the compressed air PA blown out from the plurality of nozzle portions 90, and when this swirling flow flows along the turbine disk 32b, sufficient torque can be applied to the turbine disk 32b. Accordingly, while cooling the turbine disk 32b to which the plurality of low-pressure turbine moving blades 32a are connected, sufficient torque can be applied to the turbine disk 32b, thereby improving turbine performance.

[0043] According to the gas turbine 100 of the present embodiment, the compressed air PA can be guided from the outside of the inner casing 50 to the first space US1 inside the partition wall portion 82 via the compressed air flow path 33a formed in the stationary blade 33.

[0044] According to the gas turbine 100 of the present embodiment, by making the second length L2 along the radial direction longer than the first length L1 along the first direction DR1 along the axis X of the outflow port 92, the length in the first direction DR1 can be shortened while maintaining the opening area of the outflow port 92, and the overall length of the gas turbine 100 can be shortened.

[0045] The gas turbines described in each embodiment above can be understood, for example, as follows. The gas turbine (100) according to the first aspect of this disclosure includes a compressor (10) having a plurality of compression blades (11) that rotate around an axis (X) and compressing external air to generate compressed air, a combustor (20) that burns the compressed air generated by the compressor together with fuel to generate combustion gas, a turbine (30) having a plurality of blades (32a) that rotate around the axis and a turbine disk (32b) to which the blades are connected, and driven by the combustion gas generated by the combustor, a rotating shaft (70) that connects the compressor and the turbine disk and is formed to extend along the axis and rotates in the rotational direction (RD), and the upstream space (US) of the turbine disk in the direction of combustion gas flow is arranged between the first space (US1) to which the compressed air is supplied and the turbine disk. The device comprises a partition (81) that divides the second space into which it is placed, and nozzles (90) that are arranged at multiple locations in the circumferential direction around the rotation axis of the partition and are formed in a tubular shape to guide the compressed air from an inlet (91) opening into the first space to an outlet (92) opening into the second space, wherein the outlet surface (OS) of the nozzles is arranged to be parallel to a first direction (DR1) along the axis, or to intersect the first direction at an angle of 10 degrees or less, and to be perpendicular to a second direction (DR1) along the tangent of a virtual circle passing through the nozzle with the axis as the center, or to be inclined at an angle of 45 degrees or less toward the inner circumference in the radial direction (RAD) connecting the axis and the nozzle with respect to the second direction.

[0046] According to the gas turbine according to the first aspect of the present disclosure, the combustion gas generated in the combustor applies a torque rotating about an axis to a moving blade connected to the turbine disk, causing the turbine disk to rotate in the rotational direction. A compressor connected via a rotating shaft generates compressed air as the turbine disk rotates, and the compressed air is supplied to a first space that is an upstream space of the turbine disk partitioned by a partition portion. The compressed air supplied to the first space flows into an inlet of the nozzle portion and is supplied from an outlet to a second space where the turbine disk is disposed.

[0047] An outflow surface on which the outlet of the nozzle portion is disposed is arranged to be parallel to a first direction along the axis or intersect the first direction at an angle of 10 degrees or less. The compressed air blown out from the nozzle portion either has no velocity component along the flow direction of the combustion gas, or has only a negligible velocity component if any. Further, the outflow surface on which the outlet of the nozzle portion is disposed is perpendicular to a second direction along a tangent to an imaginary circle passing through the nozzle portion centered on the axis, or is arranged to be inclined toward the radially inner peripheral side connecting the axis and the nozzle portion with respect to the second direction at an angle of 45 degrees or less.

[0048] Since the outflow surface is arranged to be inclined toward the radially inner peripheral side with respect to the second direction at an angle of 45 degrees or less, the compressed air blown out from the nozzle portion has a large circumferential velocity component around the axis. A swirling flow that swirls in the circumferential direction is generated by the compressed air blown out from the plurality of nozzle portions, and when this swirling flow flows along the turbine disk, sufficient torque can be applied to the turbine disk. Accordingly, while cooling the turbine disk to which the plurality of moving blades are connected, sufficient torque can be applied to the turbine disk to improve turbine performance.

[0049] The gas turbine according to the second aspect of the present disclosure, in the first aspect, further includes the following configuration. That is, the outflow surface is arranged to be inclined toward the radially inner peripheral side with respect to the second direction at an angle of 15 degrees or more.

[0050] According to the gas turbine of the second aspect of this disclosure, the outlet surface is arranged to be inclined at an angle of 15 degrees or more toward the radially inner circumference with respect to the second direction, thereby suppressing the guide of compressed air blown out from the outlet toward the outer circumference of the nozzle section relative to the axis due to centrifugal force. By suppressing the guide of compressed air toward the outer circumference of the nozzle section, it is possible to suppress the rise in temperature of the second space by causing the compressed air guided toward the outer circumference to generate a strong vortex and draw combustion gas into the second space.

[0051] A gas turbine according to a third aspect of the present disclosure further comprises the following configuration in the first aspect: the outlet surface is arranged parallel to the first direction and perpendicular to the second direction.

[0052] According to the gas turbine of the third aspect of this disclosure, since the compressed air blown out from the nozzle has only a circumferential velocity component around the axis, a swirling flow that rotates circumferentially is reliably generated by the compressed air blown out from multiple nozzles, and sufficient torque can be applied to the turbine disk as this swirling flow flows along the turbine disk.

[0053] A gas turbine according to a fourth aspect of the present disclosure further comprises the following configuration in any of the first to third aspects: a casing (50) formed in a cylindrical shape extending along the axis and positioned on the outer circumference side of the turbine with respect to the axis; a partition wall (82) formed in a cylindrical shape extending along the axis and positioned inside the casing to form the first space; and stator vanes (33) positioned at multiple locations in the circumferential direction and connecting the casing and the partition wall, wherein the stator vanes have compressed air passages (33a) formed therein that guide the compressed air from the outside of the casing to the first space inside the partition wall.

[0054] According to a gas turbine according to a fourth aspect of this disclosure, compressed air can be guided from the outside of the casing to a first space inside the partition wall through a compressed air passage formed in the stator blades.

[0055] A gas turbine according to a fifth aspect of the present disclosure further comprises the following configuration in any of the first to third aspects: the outlet is formed such that a second length (L2) in the radial direction is longer than a first length (L1) in the first direction.

[0056] According to the fifth aspect of this disclosure, by making the second length in the radial direction longer than the first length in the first direction of the outlet, the length in the first direction can be shortened while maintaining the opening area of ​​the outlet, thereby shortening the overall length of the gas turbine.

[0057] 10 Compressor 11 Rotor blades 20 Combustor 30 Turbine 31 High-pressure turbine 32 Low-pressure turbine 32a Low-pressure turbine rotor blades 32b Turbine disk 32b1 Seal arm 33 Stationary blades 33a Compressed air passage 40 Supercharger fan 50 Inner casing 60 Outer casing 70 Rotating shaft 80 Structure 81 Partition 81a Through hole 81b Seal arm 82 Bulkhead 90, 90A, 90B Nozzle 91 Inlet 91a Center 92 Outlet 100 Gas turbine CA Combustion gas CD Circumferential direction DR1 First direction DR2 Second direction EA External air OS Outlet surface PA Compressed air RAD Radial direction RD Rotational direction TL Tangential US Upstream space US1: First space; US2: Second space; VC: Virtual circle; X-axis: θ1, θ2: Angle

Claims

1. A compressor having a plurality of compression blades that rotate around an axis and compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate combustion gas; a turbine having a plurality of blades that rotate around an axis and a turbine disk to which the blades are connected, and driven by the combustion gas generated by the combustor; a rotating shaft connecting the compressor and the turbine disk and formed to extend along the axis and rotate in the rotational direction; a partition portion that divides the upstream space of the turbine disk in the flow direction of the combustion gas into a first space to which the compressed air is supplied and a second space in which the turbine disk is arranged; nozzle portions arranged at a plurality of locations in the circumferential direction around the rotating shaft of the partition portion and formed in a tubular shape to guide the compressed air from an inlet opening to the first space to an outlet opening to the second space, wherein the outlet surface where the outlet of the nozzle portion is located is A gas turbine arranged so as to be parallel to a first direction along the axis, or so as to intersect the first direction at an angle of 10 degrees or less, and so as to be perpendicular to a second direction along the tangent to a virtual circle passing through the nozzle portion with the axis as the center, or so as to be inclined at an angle of 45 degrees or less toward the inner circumference in the radial direction connecting the axis and the nozzle portion with respect to the second direction.

2. The gas turbine according to claim 1, wherein the outlet surface is inclined at an angle of 15 degrees or more toward the inner circumference in the radial direction with respect to the second direction.

3. The gas turbine according to claim 1, wherein the outlet surface is arranged parallel to the first direction and perpendicular to the second direction.

4. A gas turbine according to any one of claims 1 to 3, comprising: a casing formed in a cylindrical shape extending along the axis and positioned on the outer circumference side of the turbine with respect to the axis; a partition wall portion formed in a cylindrical shape extending along the axis and positioned inside the casing to form the first space; and stator vanes positioned at a plurality of locations in the circumferential direction and connecting the casing and the partition wall portion, wherein the stator vanes have compressed air passages formed therein for guiding compressed air from the outside of the casing to the first space inside the partition wall portion.

5. The gas turbine according to any one of claims 1 to 3, wherein the outlet is formed such that the second length in the radial direction is longer than the first length in the first direction.

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