JP2005042669A - Two-shaft gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a two-shaft gas turbine cooling a shaft to a center of a turbine rotor. <P>SOLUTION: This two-shaft gas turbine 1 has a high pressure turbine 10 connected to a compressor 3 and provided with a high pressure turbine rotor 9 rotatively driven by combustion gas 8a, a low pressure turbine 14 connected to a load 11 and provided with a low pressure turbine rotatively driven by combustion gas 8b, and an approximately disc-like pressure bulkhead 40 arranged between the high pressure turbine rotor 9 and the low pressure turbine rotor 13. The pressure bulkhead 40 is provided with an inflow opening 41 arranged on the peripheral side of the pressure bulkhead 40 and allowing cooling air to flow into, an outflow opening 42 arranged in the center part of the pressure bulkhead 40, a cooling air channel 43 arranged inside the bulkhead 40 so as to communicate the inflow opening 41 and the outflow opening 42 with each other, a guide vane 44 arranged to section the cooling air channel 43 into two or more in a peripheral direction and introducing cooling air from the inflow opening 41 to the outflow opening 42, and a cone 45 deflecting cooling air in a direction of a turbine rotor shaft. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention relates to a two-shaft gas turbine, and more particularly, to a two-shaft gas turbine that supplies cooling air to a disk cavity formed between a pressure bulkhead and a turbine rotor.

  A two-shaft gas turbine includes a compressor, a combustor that mixes and burns compressed air and fuel from the compressor, a high-pressure turbine including a high-pressure turbine rotor connected to the compressor, and a load such as a generator. And a low-pressure turbine having a low-pressure turbine rotor connected thereto. Then, the high-pressure and high-temperature combustion gas from the combustor is introduced into the high-pressure turbine, the high-pressure turbine rotor is rotationally driven by this combustion gas to drive the compressor, and the combustion gas that has passed through the high-pressure turbine is introduced into the low-pressure turbine, A low pressure turbine rotor is rotationally driven by the combustion gas to drive a load such as a generator.

  In order to improve the thermal efficiency of the gas turbine, the temperature of the combustion gas is increased, and the high-temperature portion in contact with the combustion gas in the high-pressure turbine and the low-pressure turbine has cooling air (for example, lower temperature than the combustion gas) The compressed air extracted from the compressor is introduced and cooled.

  Conventionally, for the purpose of cooling the stationary blade and the turbine rotor, for example, a casing supplied with cooling air from a cooling air source, and an annularly provided radially inner peripheral side of the casing, A plurality of stationary blades into which the cooling air is introduced, and an inner stationary blade support in which a part of the cooling air in the stationary blade is introduced into the inside of each of the stationary blades in the radial inner circumferential side A stationary blade device is proposed in which the outlet hole of the inner stationary blade support is provided in a plane parallel to the rotation axis of the turbine rotor (see, for example, Patent Document 1). . In this prior art, first, the cooling air from the cooling air source cools the stationary blade, and then a part of the cooling air is introduced from the outlet hole of the inner stationary blade support to the downstream disk of the turbine rotor. The moving blade provided on the side disk is cooled.

JP-A-9-112205

However, the prior art has the following problems.
Generally, in a two-shaft gas turbine, a substantially disc-shaped pressure partition is provided between a high-pressure turbine rotor and a low-pressure turbine rotor, and a disk cavity (space) is formed between the pressure partition and the turbine rotor. . Here, in order to supply cooling air for cooling the turbine rotor or the like to the disk cavity, for example, when the stationary blade device is provided on one side in the axial direction of the pressure partition together with the pressure partition, the high pressure turbine rotor and the low pressure turbine The axial distance from the rotor is increased, and the thermal efficiency of the gas turbine is reduced. On the other hand, for example, when the stationary blade device is provided without a pressure bulkhead, since the stationary blade device has a segment structure divided in the circumferential direction, a slight leakage occurs between the segments. Cooling air is not supplied to the center in the radial direction of the IT, and it is difficult to cool the shaft center portion of the turbine rotor.

  An object of the present invention is to provide a two-shaft gas turbine that can cool to the axial center of a turbine rotor.

  (1) In order to achieve the above object, the present invention provides a compressor, a combustor that mixes and burns compressed air and fuel from the compressor, and combustion from the combustor that is connected to the compressor. A high-pressure turbine having a high-pressure turbine rotor that is rotationally driven by gas; a low-pressure turbine that is connected to a load and is rotationally driven by the combustion gas from the high-pressure turbine; and the high-pressure turbine rotor and the low-pressure turbine In the two-shaft gas turbine having a substantially disk-shaped pressure partition provided between the rotor and the rotor, the pressure partition is provided on the radially outer peripheral side of the inlet, and the radial center of the inlet A cooling air channel provided in the outlet so as to communicate the inlet and the outlet, and the cooling air channel is provided so as to be divided into a plurality in the circumferential direction. It is, and a first guide means for guiding the outlet of the cooling air from the inlet.

  In the two-shaft gas turbine, a substantially disk-shaped pressure partition is provided between the high-pressure turbine rotor and the low-pressure turbine rotor, and a disk cavity is formed between the pressure partition and the turbine rotor to the axial center of the turbine rotor. Has been. In the present invention, cooling air flows in from the inlet on the radially outer peripheral side of the pressure bulkhead, and flows out from the outlet in the central portion in the radial direction to the disk cavity through the cooling air flow path inside. Thereby, it can cool to the axial center part of a turbine rotor. Further, at this time, the cooling air in the cooling air flow path is guided to the outlet by the first guide means provided by dividing the cooling air flow path into a plurality of circumferential directions. The pressure loss can be reduced as compared with the case where it is not provided.

  (2) In order to achieve the above object, the present invention is also directed to a compressor, a combustor that mixes and burns compressed air and fuel from the compressor, and the compressor connected to the combustor. A high-pressure turbine having a high-pressure turbine rotor that is rotationally driven by combustion gas; a low-pressure turbine that is connected to a load and is rotationally driven by the combustion gas from the high-pressure turbine; and the high-pressure turbine rotor and the low-pressure turbine In the two-shaft gas turbine having a substantially disc-shaped pressure partition provided between the turbine rotor and the pressure rotor, the pressure partition is provided on the radially outer peripheral side of the inlet, and the radial center of the inlet. An outlet provided in a portion, a cooling air flow path provided therein so as to communicate the inlet and the outlet, and provided on the outlet side of the cooling air flow path, Care 却空 and a second guide means for turning the turbine rotor axial direction.

  In the present invention, similarly to the above (1), it is possible to cool to the axial center of the high-pressure turbine rotor and the low-pressure turbine rotor. Further, the cooling air flowing in from the inlet on the radially outer peripheral side of the pressure bulkhead is turned in the turbine rotor axial direction by the second guide means provided on the outlet side (radially central portion) of the cooling air flow path. Since it flows out from an outflow port, the collision mixing of the cooling air in a radial direction center part can be eliminated, and pressure loss can be reduced.

  (3) In order to achieve the above object, the present invention also provides a compressor, a combustor that mixes and burns compressed air and fuel from the compressor, and the compressor connected to the combustor. A high-pressure turbine having a high-pressure turbine rotor that is rotationally driven by combustion gas; a low-pressure turbine that is connected to a load and is rotationally driven by the combustion gas from the high-pressure turbine; and the high-pressure turbine rotor and the low-pressure turbine In the two-shaft gas turbine having a substantially disc-shaped pressure partition provided between the turbine rotor and the pressure rotor, the pressure partition is provided on the radially outer peripheral side of the inlet, and the radial center of the inlet. An outlet provided in a section, a cooling air passage provided in the interior so as to communicate the inlet and the outlet, and the cooling air passage is divided into a plurality in the circumferential direction. A first guide means for guiding the cooling air from the inlet to the outlet, and a second guide means provided on the outlet side of the cooling air flow path for turning the cooling air in the turbine rotor axial direction. Guide means.

  (4) In the above (1) or (2), preferably, the first guide means is guide means that guides the cooling air so that the cooling air is in the same turning direction as the turbine rotor rotation direction at the outlet.

  As a result, the relative speed between the cooling air outflow speed from the outlet of the pressure bulkhead and the rotational speed of the turbine rotor is reduced, so that the rotational load (windage loss) of the turbine rotor can be reduced.

  According to the present invention, the cooling air flows in from the inlet on the radially outer side of the pressure partition wall, and flows out from the outlet in the central portion in the radial direction to the disk cavity through the cooling air flow path inside. Thereby, it can cool to the axial center part of a turbine rotor.

  Hereinafter, an embodiment of the present invention will be described with reference to the drawings.

  FIG. 2 is a circuit diagram showing a schematic configuration of an embodiment of the two-shaft gas turbine of the present invention.

  In FIG. 2, a two-shaft gas turbine 1 mainly includes a compressor 3 that compresses intake air 2a that is taken in to generate compressed air 2b, a combustor 5 that mixes and burns compressed air 2b and fuel 4, and A high-pressure turbine rotor 9 (see FIG. 1 to be described later) connected to a compressor rotor 6 (see FIG. 1 to be described later) of the compressor 3 through an intermediate shaft 7 and driven to rotate by a high-temperature and high-pressure combustion gas 8a from the combustor 5. And a low-pressure turbine rotor 13 (see FIG. 1 to be described later) that is connected to a load 11 such as a generator via a connecting shaft 12 and is driven to rotate by a combustion gas 8b that has passed through the high-pressure turbine 10. And a low-pressure turbine 14. The compressor rotor 6 and the high-pressure turbine rotor 9 are rotatably supported by bearings 16A and 16B provided on the front shaft 15 and the intermediate shaft 7 on the upstream side (left side in FIG. 2) of the compressor rotor 6, respectively. The rotor 13 is rotatably supported by bearings 17A and 17B provided on the connecting shaft 12.

  Then, the high-pressure turbine rotor 9 is rotationally driven by the combustion gas 8 a introduced from the combustor 5 into the high-pressure turbine 10, and the compressor rotor 6 is rotationally driven along with this to generate compressed air 2 b, which passes through the high-pressure turbine 10. The low-pressure turbine rotor 13 is rotationally driven by the combustion gas 8b introduced into the low-pressure turbine 14 to drive a load 11 such as a generator. The combustion gas 8c that has passed through the low-pressure turbine 14 is discharged after being guided to, for example, a purification device.

  FIG. 1 is a partial cross-sectional view showing a detailed structure of the two-shaft gas turbine 1 according to the present embodiment. In FIG. 1, the intake air 2a, the compressed air 2b, and the combustion gases 8a, 8b, and 8c flow from the upstream side (left side in FIG. 1) to the downstream side (right side in FIG. 1).

  In FIG. 1, the compressor 3 includes the compressor rotor 6 and a casing 18 that covers a radially outer peripheral side (upper side in FIG. 1) of the compressor rotor 6. The compressor rotor 6 includes a plurality of annularly arranged rotor blades 19, a hollow or solid compressor disk 20 in which these rotor blades 19 are implanted on the outer peripheral side in the radial direction, and the compressor disks 20 in the axial direction ( Stacking bolts 21 that are stacked in a plurality of stages (in the left-right direction in FIG. 1) and fasten to the upstream flange 7a of the intermediate shaft 7 are provided.

  On the radially inner peripheral side (lower side in FIG. 1) of the casing 18, a plurality of stationary blades 22 arranged in a ring shape are provided between the rotor blades 19 of each stage. The rotor blades 19 and the stationary blades 22 form one paragraph as a set adjacent to each other in the axial direction. In this embodiment, the rotor blades 19 and the stationary blades 22 are constituted by, for example, 15 paragraphs (however, for convenience, 8 paragraphs are shown in FIG. 2). . The intake air 2 a taken into the compressed air flow path 23 is gradually compressed in each stage, and the compressed air 2 b compressed to a predetermined pressure in the final stage is supplied to the combustor 5.

  The high-pressure turbine 10 has, for example, two stages of the high-pressure turbine rotor 9, and the low-pressure turbine 14 has, for example, two stages of the low-pressure turbine rotor 13, and the diameters of the high-pressure turbine rotor 9 and the low-pressure turbine rotor 13 are A casing 24 that covers the outer peripheral side in the direction is provided.

  The high-pressure turbine rotor 9 includes a plurality of first-stage and second-stage rotor blades 25a, 25b arranged in an annular shape, and first-stage and second-stage rotors in which the rotor blades 25a, 25b are implanted on the radially outer side. The turbine disks 26a and 26b, the hollow spacer 27 sandwiched between the turbine disks 26a and 26b, the turbine disks 26a and 26b, and the spacer 27 are stacked in the axial direction, and the downstream flange 7b of the intermediate shaft 7 is stacked. And a stacking bolt 28 to be fastened. A high-pressure disk cavity (space) 29a is formed by the hollow portion of the spacer 27 and the first and second stage turbine disks 26a and 26b.

  The low-pressure turbine rotor 13 includes a plurality of third-stage and fourth-stage rotor blades 30a, 30b arranged in an annular shape, and third-stage and fourth-stage rotor blades 30a, 30b provided on the outer peripheral side in the radial direction. The turbine disks 31a and 31b, the spacer 32 sandwiched between the turbine disks 31a and 31b, the turbine disks 31a and 31b and the spacer 32 are stacked in the axial direction, and fastened to the upstream flange 12a of the connecting shaft 12 Stacking bolts 33 are provided. A low-pressure disk cavity (space) 34a is formed by the hollow portion of the spacer 32 and the third and fourth stage turbine disks 31a and 31b.

  On the inner peripheral side of the casing 24, a plurality of first to fourth stage stationary blades 35a, 35b, 36a, 36b are provided in a ring shape between the rotor blades 25a, 25b, 30a, 30b of each stage. ing. Then, the combustion gas 8a from the combustor 5 is supplied to the combustion gas flow path 37 of the high-pressure turbine 10, and is expanded by the first stage stationary blade 35a and the moving blade 25a, and the second stage stationary blade 35b and the moving blade 25b. Work is applied to the high-pressure turbine rotor 9 to provide shaft power. Thereby, the high-pressure turbine rotor 9 and the connected compressor rotor 6 are rotationally driven. Further, the combustion gas 8b that has passed through the high-pressure turbine 10 is introduced into the combustion gas flow path 37 of the low-pressure turbine 14, and the third-stage stationary blade 36a and the moving blade 30a, and the fourth-stage stationary blade 36b and the moving blade 30b. A shaft power is given to the low-pressure turbine rotor 13 by performing expansion work. Thereby, the low-pressure turbine rotor 13 is rotationally driven.

  The stationary blades 35a, 35b, 36a, 36b and the moving blades 25a, 25b, 30a, 30b, etc. in the high-pressure turbine 10 and the low-pressure turbine 14 are placed in the combustion gas flow path 37 and become high temperature. Compressed air or the like is introduced and cooled as cooling air. In the compressed air flow path 23, a low-pressure bleed slit (not shown) provided on the outer peripheral side and a medium-pressure bleed slit provided on the outer peripheral side in order along the flow direction of compressed air (the right direction in FIG. 1). (Not shown), and a high-pressure bleed slit 38 provided on the inner peripheral side thereof.

  For example, the first stage stationary blade 35a is cooled by introducing a part of the compressed air 2b through the combustor casing 39 provided in the casing 24, and the second stage and third stage stationary blades 35b. 36a is cooled by introducing the cooling air extracted from the medium pressure extraction slit from the radially outer peripheral side, and the fourth stage stationary blade 36b has the diameter of the cooling air extracted from the low pressure extraction slit. It is introduced from the outer periphery side in the direction and cooled. The cooling air extracted from the high-pressure bleed slit 38 is introduced into the high-pressure disk cavity 29a through the hollow portion of the intermediate shaft 7 and the hollow portion of the first stage turbine disk 26a, and the shaft center portion of the high-pressure turbine rotor 9 is introduced. Is cooled and then introduced into the first and second stage rotor blades 25a and 25b via the cooling air flow paths (not shown) of the first and second stage turbine disks 26a and 26b so as to be cooled. It has become.

  Between the high-pressure turbine rotor 9 and the low-pressure turbine rotor 13, a substantially disc-shaped pressure partition 40 is provided on the inner peripheral side of the third stage stationary blade 36 a, and the pressure partition 40 has an axial cross section. For example, it is formed in an arch shape (a shape curved in the axial direction). A high pressure disk cavity 29b is formed between the pressure partition 40 and the second stage turbine disk 26b, and a low pressure disk cavity 34b is formed between the pressure partition 40 and the third stage turbine disk 31a. Yes. Further, the high pressure disk cavities 29a and 29b communicate with each other through the hollow portion of the second stage turbine disk 26b, and the low pressure disk cavities 34a and 34b communicate with each other through the hollow portion of the third stage turbine disk 31a.

  FIG. 3 is a side view seen from the direction of arrow III in FIG. 1 and shows the detailed structure of the pressure partition wall 40.

  In FIG. 3 and FIG. 1 described above, the pressure partition wall 40 is provided on the radially outer peripheral side (upper side in the drawing) and has an inlet 41 through which cooling air flows, and its radial center (lower side in FIG. 1). ) To the low-pressure disk cavity 34b side (right side in FIG. 1), an outlet 42 provided therein, a cooling air passage 43 provided therein so as to communicate with the inlet 41 and the outlet 42, The cooling air channel 43 is provided so as to be divided into, for example, eight in the circumferential direction, and for example, eight guide vanes 44 that guide the cooling air from the inlet 41 to the outlet 42 and the outlet 42 side of the cooling air channel 43 (For example, a substantially conical cone 45) that is provided on the lower side in FIG. 1 and turns the cooling air in the turbine rotor axial direction (left and right direction in FIG. 1).

  The guide vanes 44 are provided, for example, in a substantially straight linear guide portion 44a provided in the radial direction of the pressure bulkhead 40, and on the outlet 42 side of the linear guide portion 44a, and in the turbine rotor rotation direction (clockwise in FIG. 3). And a turning guide portion 44b curved in the direction).

  Then, the cooling air flowing into the inlet 41 on the radially outer peripheral side of the pressure bulkhead 40 from the third stage stationary blade 36 a is guided to the central portion in the radial direction by the linear guide portion 44 a of the guide vane 44, and The turning guide portion 44b turns in the same turning direction as the turbine rotor rotation direction, and the cone 45 turns in the turbine rotor axial direction, and flows out from the outlet 42 in the radial center to the low pressure disk cavity 34b. .

  A part of the cooling air in the low-pressure disk cavity 34b is introduced into the low-pressure disk cavity 34a, and the third stage is passed through the cooling air flow paths (not shown) of the third and fourth stage turbine disks 31a and 31b. And it is introduced into the fourth stage blades 36a, 36b and rejected. The remainder of the cooling air in the low-pressure disk cavity 34b joins the combustion gas passage 37 as sealing air.

  In the above, the guide vane 44 is provided so as to divide the cooling air flow path described in each claim into a plurality of circumferential directions, and constitutes a first guide means for guiding the cooling air from the inlet to the outlet. The turning guide portion 44b of the guide vane 44 constitutes a guide means that guides the cooling air described in each claim so that the cooling air is in the same turning direction as the turbine rotor rotation direction at the outlet. The cone 45 is provided on the outlet side of the cooling air flow path, and constitutes second guide means for turning the cooling air in the turbine rotor axial direction.

Next, the operation and effect of this embodiment will be described.
Along with the operation of the two-shaft gas turbine 1, the compressor 3 generates compressed air 2 b that is compressed to a predetermined pressure by the rotation of the compressor rotor 6, and the combustor 5 generates the compressed air 2 b and the fuel 4. Are combusted to produce combustion gas 8a. In the high pressure turbine 10, the high pressure turbine rotor 9 is rotationally driven by the combustion gas 8a passing through the first stage stationary blades 35a and the moving blades 25a, and the second stage stationary blades 35b and the moving blades 25b. The rotor 6 is driven to rotate, and the low-pressure turbine rotor 13 is rotated by the low-pressure turbine 14 by the combustion gas 8b passing through the third-stage stationary blade 36a and the moving blade 30a, and the fourth-stage stationary blade 36b and the moving blade 30b. Driven to drive a load 11 such as a generator.

  During the operation of the two-shaft gas turbine 1, the stationary blades 35a, 35b, 36a, 36b and the moving blades 25a, 25b, 30a, 30b are heated by the combustion gases 8a, 8b. The cooled air is introduced and cooled. Cooling air from the high pressure bleed slit 38 is applied to the first stage stationary blade 35a, cooling air from the intermediate pressure bleed slit is applied to the second and third stage stationary blades 35b and 36a, and the fourth stage stationary blade. Cooling air from the low-pressure extraction slit is introduced into 36b for cooling. Further, the cooling air 26 from the high-pressure bleed slit 38 is introduced into the high-pressure disk cavity 29a, and the shaft center portion of the high-pressure turbine rotor 9 is cooled.

  In the present embodiment, the cooling air that has cooled the third stage stationary blade 36 a flows in from the inlet 41 on the radially outer peripheral side of the pressure partition wall 40, passes through the cooling air flow path 43 inside, and is centered in the radial direction. From the outlet 42 to the low-pressure disk cavity 34b. Thereby, it can cool to the axial center part of the low pressure turbine rotor 13. At this time, since the cooling air in the cooling air flow path 43 is guided to the outlet 42 by the guide vane 44, for example, pressure loss can be reduced compared to the case where the guide vane 44 is not provided. Further, the cooling air flowing in from the inlet 41 on the radially outer peripheral side of the pressure partition wall 40 is turned in the axial direction of the low-pressure turbine rotor 13 by the cone 45 provided on the outlet 42 side of the cooling air passage 43. The collision loss of cooling air can be eliminated and the pressure loss can be reduced.

  Further, the cooling air from the outlet 42 of the pressure bulkhead 40 has the same turning direction as the rotation direction of the low-pressure turbine rotor 13 by the turning guide portion 44 b of the guide vane 44. The relative speed with respect to the rotational speed is reduced, and the rotational load (windage loss) of the low-pressure turbine rotor 13 can be reduced.

  The pressure bulkhead 40 has a static pressure equivalent to the upstream static pressure of the third stage stationary blade 36a on the upstream side surface thereof, and the downstream side static pressure of the third stage stationary blade 36a on the downstream side surface. Equivalent static pressure is applied, and the strength to withstand the force corresponding to these differential pressures must be ensured. In this embodiment, although the cooling air flow path 43 is formed inside the pressure partition wall 40, the plurality of guide vanes 44 also serve as reinforcing members, so that the rigidity of the pressure partition wall 40 can be increased.

  In the two-shaft gas turbine 1 according to the present embodiment, since the pressure loss of the cooling air flow path 43 of the pressure partition 40 can be reduced as described above, the supply pressure for securing a predetermined flow rate of cooling air ( That is, the bleed pressure from the compressor 3) can be reduced and the driving force of the compressor 3 can be reduced. Further, when the extraction pressure from the compressor 3 is reduced, the temperature of the cooling air itself is lowered, so that the extraction flow rate of the cooling air can be reduced and the flow rates of the fuel gases 2a and 2b can be increased. it can. Therefore, the thermal efficiency of the two-shaft gas turbine 1 can be improved. Further, by reducing the pressure loss, the flow passage area of the pressure bulkhead 40 or the third stage stationary blade 36a, for example, can be reduced, and the components can be reduced.

  In the above-described embodiment, the guide vane 44 as the first guide means has been described by taking a structure including the straight guide portion 44a and the turning guide portion 44b as an example. However, the present invention is not limited to this. That is, for example, without providing the turning guide portion 44b that guides the cooling air so as to be in the same turning direction as the turbine rotor rotation direction, as shown in FIG. 4 corresponding to FIG. It is good also as guide vane 44 'provided so that cooling air flow path 43' may be formed. In this case, the guide vane 44 'is larger than that in the above-described embodiment, and the rigidity can be increased. In the above embodiment, the pressure bulkhead 40 has been described by taking as an example a structure in which both the guide vane 44 as the first guide means and the cone 45 as the second guide means are provided. For example, only one of the guide vane 44 and the cone 45 may be provided. In these cases, the same effect as described above is obtained.

  In the above-described embodiment, the substantially disk-shaped pressure bulkhead 40 has been described by taking an example in which the axial cross section has an arch shape, but is not limited thereto. That is, for example, if the strength can be secured like the pressure partition wall 44 ′ shown in FIG. 4, the axial section of the pressure partition wall 40 ′ is substantially linear as shown in FIG. 5 corresponding to FIG. It is good. In this case, since the axial dimension of the pressure partition 40 'can be reduced as compared with the above-described embodiment, the axial distance between the high-pressure turbine rotor 9 and the low-pressure turbine rotor 13 is reduced, and the two-shaft gas The thermal efficiency of the turbine 1 can be improved.

  Further, in the above-described embodiment and modification, the explanation has been given by taking as an example the structure in which the outlet 41 of the pressure partition 40 opens only on the low-pressure disk cavity 34b side, but the present invention is not limited to this. That is, for example, a structure that opens to the high-pressure disk cavity 29b side or a structure that both the low-pressure disk cavity 34b side and the high-pressure disk cavity 29b side open may be used. In these cases, the same effect as described above is obtained.

It is a fragmentary sectional view showing the detailed structure of one Embodiment of the 2-shaft type gas turbine of this invention. 1 is a circuit diagram illustrating a schematic configuration of an embodiment of a two-shaft gas turbine of the present invention. FIG. 3 is an axial side view seen from the direction of arrow III in FIG. 1 and shows a detailed structure of a pressure bulkhead constituting one embodiment of the two-shaft gas turbine of the present invention. It is an axial side view showing the detailed structure of the pressure partition which comprises the modification of the biaxial gas turbine of this invention. It is a fragmentary sectional view showing the detailed structure of the modification of the 2-shaft type gas turbine of this invention.

Explanation of symbols

1 Two-shaft gas turbine 2b Compressed air 3 Compressor 4 Fuel 5 Combustor 8a Combustion gas 8b Combustion gas 9 High pressure turbine rotor 10 High pressure turbine 13 Low pressure turbine rotor 14 Low pressure turbine 40 Pressure partition 41 Inlet 42 Outlet 43 Cooling air flow Road 44 guide vane (first guide means)
45 cone (second guide means)

Claims (4)

A compressor, a combustor that mixes and burns compressed air and fuel from the compressor, a high-pressure turbine that is connected to the compressor and includes a high-pressure turbine rotor that is rotationally driven by combustion gas from the combustor; A low pressure turbine having a low pressure turbine rotor connected to a load and rotationally driven by the combustion gas from the high pressure turbine, and a substantially disc-shaped pressure partition wall provided between the high pressure turbine rotor and the low pressure turbine rotor. A two-shaft gas turbine having
The pressure bulkhead is provided in the radially outer peripheral side thereof so that the inlet into which cooling air flows in, the outlet provided in the center in the radial direction, and the inlet and the outlet are in communication with each other. A cooling air flow path provided; and a first guide means provided so as to divide the cooling air flow path into a plurality of circumferential directions and guiding the cooling air from the inlet to the outlet. A two-shaft gas turbine. A compressor, a combustor that mixes and burns compressed air and fuel from the compressor, a high-pressure turbine that is connected to the compressor and includes a high-pressure turbine rotor that is rotationally driven by combustion gas from the combustor; A low pressure turbine having a low pressure turbine rotor connected to a load and rotationally driven by the combustion gas from the high pressure turbine, and a substantially disc-shaped pressure partition wall provided between the high pressure turbine rotor and the low pressure turbine rotor. A two-shaft gas turbine having
The pressure bulkhead is provided in the radially outer peripheral side thereof so that the inlet into which cooling air flows in, the outlet provided in the center in the radial direction, and the inlet and the outlet are in communication with each other. A biaxial gas comprising: a provided cooling air flow path; and a second guide means provided on the outlet side of the cooling air flow path to turn the cooling air in a turbine rotor axial direction. Turbine. A compressor, a combustor that mixes and burns compressed air and fuel from the compressor, a high-pressure turbine that is connected to the compressor and includes a high-pressure turbine rotor that is rotationally driven by combustion gas from the combustor; A low pressure turbine having a low pressure turbine rotor connected to a load and driven to rotate by the combustion gas from the high pressure turbine; and a substantially disc-shaped pressure partition provided between the high pressure turbine rotor and the low pressure turbine rotor. A two-shaft gas turbine having
The pressure bulkhead is provided in the radially outer peripheral side thereof so that the inlet into which cooling air flows in, the outlet provided in the center in the radial direction, and the inlet and the outlet are in communication with each other. A provided cooling air flow path, a first guide means provided to divide the cooling air flow path into a plurality of circumferential directions, and guiding the cooling air from the inlet to the outlet; and the cooling air flow A two-shaft gas turbine comprising: second guide means provided on the outlet side of the passage and configured to turn the cooling air in a turbine rotor axial direction. 4. The two-shaft gas turbine according to claim 1, wherein the first guide means is a guide means for guiding the cooling air so that the cooling air has the same turning direction as a turbine rotor rotation direction at the outlet. 5. A two-shaft gas turbine.

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