JP5901360B2 - Turbine cooling structure and gas turbine - Google Patents

Description

  The present invention relates to a turbine cooling structure and a gas turbine.

  In recent gas turbines, in order to achieve high output and high efficiency, the temperature of the combustion gas led to the turbine stationary blade and the turbine rotor blade tends to increase. Therefore, a cooling medium such as air or steam is supplied to the cooling flow passages inside the turbine stator blade and the turbine rotor blade for the purpose of ensuring heat resistance in the turbine stator blade and the turbine rotor blade.

As described above, in order to supply a cooling medium, for example, cooling air, to the cooling flow path of the turbine blade, the cooling air is introduced into the rotating rotor from the air storage chamber provided on the stationary casing side. Has been.
Simply, when cooling air is introduced from the stationary reservoir into the rotating rotor, energy loss occurs when cooling air that does not have a flow velocity component in the rotor rotation direction flows into the rotor. (Pumping loss) occurs, and the performance of the gas turbine deteriorates.

In order to suppress the occurrence of such a pumping loss, conventionally, a flow velocity component (swirl flow) in the rotational direction of the rotor is preliminarily applied to the cooling air flowing into the rotor rotating from the stationary reservoir chamber. There has been proposed a technique in which a swivel (Pre-swirl) nozzle or a TOBI (Tangential OnBoard Injection) nozzle is provided (see, for example, Patent Document 1).
Then, the above-mentioned pumping loss is generated by applying a swirling flow to the cooling air by the pre-swirl nozzle or the TOBI nozzle to reduce the difference between the rotational velocity component of the cooling air and the rotational speed of the rotor. Is suppressed.

JP 2010-196501 A

  However, since the pumping loss described above may occur due to the complicated structure of the turbine, the pumping loss cannot be sufficiently eliminated by simply providing the pre-swivel nozzle and the TOBI nozzle as in the conventional case. There is a problem. That is, it is required to further suppress the occurrence of pumping loss based on the turbine structure.

  The present invention has been made in view of the above-described circumstances, and an object of the present invention is to provide a turbine cooling structure and a gas turbine capable of suppressing the generation of pumping loss based on the turbine structure and suppressing the performance degradation of the turbine.

In order to solve this problem, a turbine cooling structure according to the present invention includes a turbine disk in which a plurality of rotor blades are attached to an outer peripheral portion side by side in the circumferential direction, and supported rotatably around an axis, and the turbine disk. A cooling hole for supplying a cooling medium to the cooling flow path inside the rotor blade, and a cylindrical shape centering on the axis, and the cooling medium is supplied from the outside. A cylindrical partition portion that partitions the first inlet space and the second inlet space communicated with the cooling hole, and the interior of the cylindrical partition portion is directed from the first inlet space toward the second inlet space. A supply passage that extends and supplies the cooling medium from the first inlet space to the second inlet space, and an annular shape centering on the axis, and the second inlet space of the supply passage Side opening Provided, to the cooling medium flowing from the first inlet space to the axial direction toward the second inlet space, and an annular nozzle member for applying a swirling flow which rotates the turbine disk in the same direction, the The annular nozzle member is composed of a plurality of nozzle divided bodies divided in the circumferential direction, and a seal member is provided in a gap between two nozzle divided bodies adjacent in the circumferential direction so as to block the gap in the axial direction. It is characterized by being.

In the turbine cooling structure, as in the conventional case, the cooling medium flows from the supply channel through the annular nozzle member into the second inlet space, so that a swirling flow is imparted to the cooling medium.
However, when the annular nozzle member is constituted by a plurality of nozzle divided bodies as described above, the cooling medium in the supply flow path passes through the gap between two adjacent nozzle divided bodies and enters the second inlet space. May flow in. And since the swirl flow is not given to the cooling medium that has passed through this gap, the cooling air to which the swirl flow is given and the cooling air to which no swirl flow is given are mixed, and the flow velocity component in the rotation direction in the cooling medium Will be slowed down. In other words, the swirl flow of the cooling medium flowing from the supply flow path into the second inlet space is disturbed. As a result, energy loss (pumping loss) occurs when the cooling medium enters the cooling hole of the rotating turbine disk from the second inlet space.

  On the other hand, according to the cooling structure, since the seal member that fills the gap is provided in the gap between the two nozzle divided bodies, the gap between the two nozzle divided bodies adjacent to the cooling medium in the supply flow path is provided. It can prevent flowing into the 2nd entrance space through. Thereby, it is possible to suppress the occurrence of turbulence in the swirling flow of the cooling medium flowing into the second inlet space from the supply flow path through the annular nozzle member, and it is possible to suppress the occurrence of the above-described pumping loss.

  In the turbine cooling structure, at least one nozzle divided body of the two nozzle divided bodies is recessed from the dividing surface of the one nozzle divided body that defines the gap together with the other nozzle divided body. A housing recess for housing a part of the seal portion may be formed.

  In the turbine cooling structure, it is further preferable that the housing recess is formed in the two nozzle divided bodies, and the seal member is housed in the two housing recesses.

In these turbine cooling structures, even if the seal member is not fixed to the nozzle divided body, a part of the seal member is housed and held in the housing recess, so that the seal member flows into the gap from the supply flow path. It is possible to prevent the cooling medium from flowing out of the gap into the second inlet space.
In particular, when the same seal member is housed in both of the two housing recesses formed in the two nozzle divided bodies, it can be more reliably prevented from falling out of the gap into the second inlet space. Further, in this case, the seal member is pressed against the inner surfaces of the two housing portions by the flow of the cooling medium flowing into the gap from the supply flow path, thereby blocking the gap in the flow direction of the cooling medium and supplying the supply flow path. It is possible to prevent the inside cooling medium from flowing into the second inlet space through the gap between two adjacent nozzle divided bodies.

  Furthermore, in the cooling structure of the turbine, the seal member is formed in a plate shape, and the plate thickness direction of the seal member is along the flow direction of the cooling medium flowing into the gap from the supply flow path. When accommodated in the two accommodating recesses, the width dimension of the accommodating recess along the flow direction of the cooling medium is set to be larger than the plate thickness dimension of the seal member, and faces each other along the circumferential direction. It is preferable that the distance between the bottom portions of the two housing recesses is set to be larger than the height dimension of the seal member along the circumferential direction.

According to this turbine cooling structure, for example, when the relative positions of the two receiving recesses along the flow direction of the cooling medium coincide with each other, the flow direction of the cooling medium is between the seal member and the inner surface of the receiving recess. A gap along the circumferential direction and a gap along the circumferential direction are generated.
Because of the existence of these gaps, for example, when the two nozzle divided bodies are displaced from each other in the flow direction of the cooling medium, that is, when the relative positions of the two housing recesses are displaced from each other in the flow direction of the cooling medium. The seal member can be inclined in the flow direction of the cooling medium with respect to the circumferential direction of the annular seal member while maintaining the state of being accommodated in the two accommodating recesses. Thereby, the shift | offset | difference to the said flow direction of the relative position of two accommodating recessed parts can be accept | permitted.

Therefore, when two nozzle division bodies try to shift | deviate mutually with respect to the flow direction of a cooling medium, it can suppress that a stress arises in a plate-shaped sealing member or an accommodation recessed part. Therefore, even if the seal member is made of a highly rigid material that is difficult to be elastically deformed, the seal member and the housing recess can be protected.
Even if the seal member is inclined obliquely as described above, the seal member is held in the state of being accommodated in the two accommodating recesses, so even if the seal member is formed of a highly rigid material, the seal member Thus, it is possible to prevent the gas from flowing into the second inlet space through the gap between the two nozzle divided bodies.

  Moreover, in the cooling structure of the turbine, when the seal member is formed in a plate shape, at least one of corner portions located on the downstream side in the flow direction of the cooling medium is rounded among the seal members. It is more preferable.

  When the plate-like seal member is inclined obliquely as described above, the corner located on the downstream side in the flow direction of the cooling medium may be pressed against the inner surface of the housing recess. Since this is rounded, the adhesion between the corner and the inner surface of the housing recess is improved as compared with the case where the sharp corner hits the inner surface of the housing recess. Therefore, even if it is a plate-shaped sealing member, it can prevent more reliably that a cooling medium flows into the 2nd inlet space through the clearance gap between two nozzle division bodies.

  Furthermore, in the cooling structure of the turbine, the seal member may be formed of an elastic body that can be elastically deformed.

In the above configuration, since the seal member is elastically deformed and inserted into the gap between the two nozzle divided bodies, the seal member is pressed against the two nozzle divided bodies by its elastic force. It is possible to reliably prevent the cooling medium in the flow path from passing through the gap between two adjacent nozzle divided bodies and flowing into the second inlet space.
It is also possible to hold the seal member in the gap between the two nozzle divided bodies by the elastic force of the elastically deformed seal member.

  Further, in the cooling structure of the turbine, the annular nozzle member includes a plurality of airfoil portions arranged in a circumferential direction thereof to impart the swirl flow to the cooling medium, and one airfoil portion includes the two airfoil portions. In the portion where the thickness of the one airfoil portion is formed to be the thickest along the flow direction of the cooling medium that is divided into two nozzle divided bodies and flows into the gap from the supply flow path, the one airfoil portion is It should be divided.

  In the turbine cooling structure, the sealing member is disposed in the gap between the divided one airfoil, and this one airfoil is formed in one airfoil along the flow direction of the cooling medium. By dividing at the portion where the thickness is the thickest, it is possible to secure the maximum area for filling the gap between the two nozzle divided bodies by the seal member. Therefore, it can prevent more reliably that a cooling medium flows into the 2nd entrance space through the clearance gap between two nozzle division bodies.

  The gas turbine according to the present invention includes a compression section that sucks and compresses air, a combustion section that generates a combustion gas by burning an air-fuel mixture composed of compressed air and fuel supplied from outside. And a turbine section for extracting a rotational driving force from the combustion gas. The turbine section is provided with a cooling structure for the turbine.

  According to the present invention, it is possible to suppress the occurrence of pumping loss based on the structure of the annular nozzle member constituting the cooling structure of the turbine, particularly the structure in which a gap is formed between the two nozzle divided bodies. The performance degradation of the turbine based on can be suppressed.

It is a mimetic diagram showing a gas turbine concerning a first embodiment of the present invention. It is a fragmentary sectional view of the turbine part of FIG. It is a partial expanded sectional view which shows the structure of the 1st stage | paragraph rotor blade periphery among the turbine parts of FIG. It is the schematic front view which looked at the inner side partition part and annular nozzle member shown to FIG.2, 3 from the exit cavity (2nd inlet space) side. It is a principal part enlarged front view which shows the part of the principal part I among the cyclic | annular nozzle members shown in FIG. It is the principal part enlarged view which looked at the annular nozzle member shown in FIG. 5 from the inner ring | wheel part side. It is AA arrow sectional drawing of FIG. FIG. 8 is an enlarged cross-sectional view showing a main part of the seal member and the housing recess of the divided body in FIG. The state which has shifted | deviated is shown. It is a principal part expanded sectional view which shows the sealing member provided in the cyclic | annular nozzle member which comprises the gas turbine which concerns on 2nd embodiment of this invention, (a) shows the state where the two accommodation recessed parts are facing, b) shows a state in which the two receiving recesses are displaced in the flow direction. It is a principal part expanded sectional view which shows the seal member provided in the cyclic | annular nozzle member which comprises the gas turbine which concerns on 3rd embodiment of this invention. It is a principal part expanded sectional view which shows the sealing member provided in the cyclic | annular nozzle member which comprises the gas turbine which concerns on 4th embodiment of this invention. It is a principal part expanded sectional view which shows the sealing member provided in the cyclic | annular nozzle member which comprises the gas turbine which concerns on 5th embodiment of this invention. It is a principal part expanded sectional view which shows the sealing member provided in the annular nozzle member which comprises the gas turbine which concerns on other embodiment of this invention. It is a principal part expanded sectional view which shows the sealing member provided in the annular nozzle member which comprises the gas turbine which concerns on other embodiment of this invention. It is a principal part expanded sectional view which shows the sealing member provided in the annular nozzle member which comprises the gas turbine which concerns on other embodiment of this invention.

[First embodiment]
Hereinafter, a first embodiment of the present invention will be described with reference to FIGS.
As shown in FIG. 1, a gas turbine 1 according to this embodiment drives a device such as a generator (not shown), for example, and includes a compressor (compression unit) 2 and a combustor (combustion unit) 3. And a turbine section 4 and a rotating shaft 5.
The compressor 2 sucks and compresses atmospheric air, which is external air, and supplies the compressed air to the combustor 3.

The combustor 3 generates high-temperature gas (combustion gas) by mixing the air compressed by the compressor 2 and fuel supplied from the outside and burning the mixed gas mixture.
The rotary shaft 5 is a columnar member that is rotatably supported around a rotation axis (axis) L, and transmits the rotational driving force generated by the turbine unit 4 to devices such as the compressor 2 and the generator. It is.
The specific configurations of the compressor 2, the combustor 3, and the rotating shaft 5 can adopt known configurations, respectively, and are not particularly limited.

The turbine unit 4 receives the supply of the high-temperature gas generated by the combustor 3 to generate a rotational driving force, and transmits the generated rotational driving force to the rotating shaft 5.
As shown in FIGS. 2 and 3, the turbine section 4 includes a first stage blade (stationary blade) 11S fixed to the casing 13S and a first stage blade (moving blade) attached to a first stage turbine disk (turbine disk) 31R. Blades) 21R, inlet cavities (first inlet spaces) 41C and outlet cavities (second inlet spaces) 42C to which cooling air (cooling medium) used for cooling the first stage blades 21R and the like is supplied, and these inlet cavities An inner partition wall (cylindrical partition) 61S that divides 41C and the outlet cavity 42C, and a rim seal cavity (rim seal space) 43C that supplies cooling air between the first stage stationary blade 11S and the first stage moving blade 21R are mainly used. Is provided.

1 is not shown in FIGS. 2 and 3, but extends in the left-right direction.
Further, in addition to the first stage stationary blade 11S, the first stage moving blade 21R, and the first stage turbine disk 31R, the turbine unit 4 includes a combustion gas flow along a rotation axis L (see FIG. 1) as shown in FIG. To the downstream side (right side in FIG. 2), a two-stage stator blade (not shown), a two-stage rotor blade 211R, a two-stage turbine disk 311R, a three-stage stator blade (not shown), a three-stage rotor blade 212R, a three-stage turbine disk 312R, etc. Here, only the vicinity of the first stage stationary blade 11S, the first stage moving blade 21R, and the first stage turbine disk 31R which are arranged near the combustor 3 and need the most cooling will be described.

As shown in FIG. 2, the first stage stationary blade 11 </ b> S generates a rotational driving force from the combustion gas generated by the combustor 3 together with the first stage moving blade 21 </ b> R. Further, the first stage stationary blade 11S extends from the casing 13S formed in a cylindrical shape centering on the rotation axis L to the inner side in the radial direction (lower side in FIG. 2), in other words, the flow path side through which the combustion gas flows. And wings arranged at equal intervals in the circumferential direction.
The first stage stationary blade 11S is arranged on the combustor 3 side (left side in FIG. 2) from the first stage moving blade 21R, in other words, on the upstream side of the combustion gas flow.

An inner shroud 12S is provided at the inner peripheral end of the first stage stationary blade 11S.
The inner shroud 12S is a plate-like member extending in the circumferential direction at the inner peripheral end of the first stage stationary blade 11S, and forms a part of a flow path through which combustion gas flows. The inner shroud 12S is fixed to an outer partition wall 51S disposed on the inner peripheral side.
The outer partition wall 51S is a member formed in a cylindrical shape centering on the rotation axis L, and constitutes part of the wall surface of the inlet cavity 41C, the rim seal cavity 43C, and the like together with the inner partition wall 61S described later. It is.

  The first stage blade 21R generates rotational driving force from the combustion gas generated by the combustor 3 together with the first stage stationary blade 11S. Further, the first stage blade 21R extends from the outer peripheral surface of the first stage turbine disk 31R formed in a disc shape to the outside in the radial direction (upper side in FIG. 2), in other words, the flow path side through which the combustion gas flows. And wings arranged at equal intervals in the circumferential direction. The first stage blade 21R is arranged downstream of the combustion gas flow from the first stage stationary blade 11S (the right side in FIG. 2).

As shown in FIG. 3, the first stage blade 21R includes a blade portion 22R, a platform 23R, a blade attachment portion 24R, and a cooling flow path 25R.
The blade portion 22R is a portion that generates a rotational driving force by receiving a flow of combustion gas. A specific shape of the wing portion 22R can be adopted and is not particularly limited.
The platform 23R is disposed at an end on the radially inner side (lower side in FIG. 3) of the wing 22R, in other words, is disposed at an end on the radially outer side of the wing mounting portion 24 described later. The platform 23R extends in the circumferential direction and forms part of a flow path through which combustion gas flows.

The blade attachment portion 24R is a portion that forms an end portion on the radially inner side of the first-stage moving blade 21R, and is a portion that is fitted to the first-stage turbine disk 31R. The radially inner end of the blade attachment portion 24R constitutes a part of a wall surface of an axial communication path 36R described later.
The cooling flow path 25R is a part that guides cooling air into the blade portion 22R and cools the blade portion 22R. The cooling flow path 25R is formed on the radially inner surface of the blade attachment portion 24R and extends from the blade attachment portion 24R to the blade portion 22R. In addition, a well-known thing can be employ | adopted for the shape and structure of the cooling flow path 25R in the inside of the wing | blade part 22R, and it is not specifically limited.

  The first-stage turbine disk 31R is a disk-shaped member centered on the rotation axis L, and is attached to the rotation shaft 5 (see FIG. 1) so as to be able to transmit a rotational driving force. The first-stage turbine disk 31R is disposed at a distance downstream of the combustion gas flow with respect to the outer partition wall 51S and the inner partition wall 61S. The above-described first stage moving blades 21R are arranged at equal intervals in the circumferential direction on the outer peripheral surface of the first stage turbine disk 31R.

The radially outer end of the first-stage turbine disk 31R is formed in a shape that fits the blade mounting portion 24R of the first-stage moving blade 21R described above, whereby the first-stage moving blade 21R becomes the first-stage turbine disk. It is fixed to 31R. Further, in a state where the first stage blade 21R is fixed to the first stage turbine disk 31R, a groove formed at the radially outer end of the first stage turbine disk 31R and the blade mounting portion 24R of the first stage blade 21R. An enclosed axial communication path 36R is defined.
The axial communication path 36R is a path disposed at a radially outer position in the first stage turbine disk 31R, and extends along the rotation axis L. The axial communication path 36R has an opening on the radially inner side of the cooling flow path 25R, whereby the axial communication path 36R is a flow path that guides cooling air to the cooling flow path 25R of the first stage blade 21R. I am doing.

The first-stage turbine disk 31R is formed with a cooling hole 33R, a disk flow path 34R, and a seal arm 35R.
The cooling hole 33R penetrates the inside of the first stage turbine disk 31R and is formed so as to guide the cooling air from the outlet cavity 42C to the cooling flow path 25R of the first stage blade 21R. It constitutes a road.
A plurality of the cooling holes 33R are arranged at equal intervals in the circumferential direction similarly to the first stage blade 21R. In other words, the cooling holes 33R are arranged at the same circumferential position as the first stage blade 21R. Then, one end portion (radially inner end portion in FIG. 3) of the cooling hole 33R is opened to an outlet cavity 42C described later, and the other end portion (radially outer end portion in FIG. 3) is the same as that described above. The axial communication path 36R is opened.
The cooling hole 33R in the illustrated example is formed by extending the inside of the first stage turbine disk 31R from the radially inner side to the radially outer side, but the relative relationship between the outlet cavity 42C and the axial communication path 36R. It may be appropriately formed depending on the position.

The disk flow path 34R is formed so as to penetrate the inside of the first stage turbine disk 31R in the direction of the rotation axis L, and the cooling air is disposed downstream of the first stage blade 21R from the outlet cavity 42C in the combustion gas flow. A flow path is provided to supply the blades (for example, the two-stage moving blade 211R and the three-stage moving blade 212R shown in FIG. 2).
The seal arm 35R is formed in a cylindrical shape extending from the upstream end of the combustion gas flow in the first stage turbine disk 31R along the rotation axis L toward the inner partition wall 61S. The seal arm 35R is located outside the outlet cavity 42C in the radial direction, and constitutes a seal structure that regulates the flow rate of cooling air flowing from the outlet cavity 42C to the rim seal cavity 43C. The seal arm 35R also constitutes a part of the wall surface of the outlet cavity 42C.
A connecting rotor 38R formed in a cylindrical shape extending in the direction of the rotation axis L is connected to the first stage turbine disk 31R configured as described above. The connection rotor 38R is located on the radially inner side of the outlet cavity 42C, in other words, is disposed with a gap on the radially inner side of the inner partition wall 61S.

  The inlet cavity 41C is a cylindrical space centering on the rotation axis L formed between the outer partition wall portion 51S and the inner partition wall portion 61S, and the combustion gas flow with respect to the outlet cavity 42C and the rim seal cavity 43C. Is located upstream (left side in FIG. 3). Further, the inlet cavity 41C is located on the radially outer side (upper side in FIG. 3) with respect to the outlet cavity 42C, and is disposed on the radially inner side (lower side in FIG. 3) with respect to the rim seal cavity 43C.

A supply flow path 52S for supplying cooling air from the outside to the inlet cavity 41C is connected to the inlet cavity 41C.
Here, the cooling air supplied from the outside to the inlet cavity 41 </ b> C through the supply flow path 52 </ b> S is, for example, air extracted from the compressor 2 and cooled. More specifically, compressed air having a pressure required to supply cooling air from the inlet cavity 41C to the cooling flow path 25R of the first stage blade 21R, or cooling from the rim seal cavity 43C to the combustion gas flow path. Compressed air having a pressure required for causing air to flow out is extracted from the compressor 2.

  The outlet cavity 42C is a cylindrical space centered on the rotation axis L formed between the inner partition wall 61S, the first stage turbine disk 31R, and the connection rotor 38R. The outlet cavity 42C is formed on the downstream side (right side in FIG. 3) of the combustion gas flow with respect to the inlet cavity 41C. Further, the position of the exit cavity 42C in the direction of the rotation axis L is set substantially the same as the position of the rim seal cavity 43C. Furthermore, the exit cavity 42C is located on the radially inner side (lower side in FIG. 3) than the entrance cavity 41C and the rim seal cavity 43C.

The outlet cavity 42C is connected to the cooling hole 33R of the first-stage turbine disk 31R described above. Thus, the outlet cavity 42C is communicated with the cooling flow path 25R of the moving blade 21R, and cooling air can be supplied into the moving blade 21R.
In addition, a disk flow path 34R of the first stage turbine disk 31R is connected to the outlet cavity 42C. Thus, the cooling air is directed from the outlet cavity 42C toward the moving blades (for example, the second-stage moving blade 211R and the third-stage moving blade 212R shown in FIG. 2) that are arranged on the downstream side of the combustion gas flow from the first-stage moving blade 21R. It can also be supplied.
Further, in the outlet cavity 42C, a space between the connecting rotor 38R and a supply passage 62S of the inner partition wall 61S described later, or an inner partition wall 61S formed on the upstream side of the combustion gas flow from the outlet cavity 42C. 44C (the bypass space 44C) is connected.

  As shown in FIG. 4, the inner partition wall 61 </ b> S is formed in a substantially cylindrical shape with the rotation axis L as the center, and is configured by a plurality of partition walls divided in the circumferential direction. If demonstrating it concretely, the inner side partition part 61S of this embodiment is comprised by two partition division body 61SA, 61SB divided | segmented in the virtual plane (horizontal division surface) containing the rotating shaft L. These two partition walls 61SA and 61SB are fastened by bolts 9 at flange portions formed to protrude radially outward of the inner partition wall portion 61S. In this fastened state, no gap is generated between the split surfaces of the two partition wall partitions 61SA and 61SB.

As shown in FIG. 3, the inner partition wall 61S of the present embodiment has a flange shape extending radially outward of the cylindrical portion at the downstream end of the combustion gas flow in the cylindrical portion. A part is formed.
The inner partition wall 61S is disposed with a gap inward in the radial direction of the outer partition wall 51S, and is disposed with a gap in the radial outer side of the connection rotor 38R. Further, the inner partition wall 61S is disposed at an upstream side in the combustion gas flow with respect to the first stage turbine disk 31R. Accordingly, the inner partition wall 61S forms the aforementioned inlet cavity 41C together with the outer partition wall 51S, and also forms the aforementioned outlet cavity 42C and bypass space 44C together with the first stage turbine disk 31R and the connecting rotor 38R. Further, the inner partition wall 61S forms a rim seal cavity 43C described later together with the outer partition wall 51S and the first stage turbine disk 31R.

The inner partition wall 61S is provided with a supply channel 62S, a partition channel 63S, a jumper tube (communication channel) 64S, and a protrusion 65S.
The supply flow path 62S is formed through the inside of the inner partition wall 61S so as to extend from the inlet cavity 41C toward the outlet cavity 42C at the downstream end of the combustion gas flow in the inner partition wall 61S. Yes. That is, the supply flow path 62S forms a flow path that connects the inlet cavity 41C and the outlet cavity 42C to each other and supplies cooling air from the inlet cavity 41C to the outlet cavity 42C.
In the present embodiment, the supply flow path 62S is inclined so as to go radially inward as it goes downstream of the combustion gas flow. Further, the opening of the supply flow path 62S with respect to the outlet cavity 42C faces the downstream side of the combustion gas flow in the inner partition wall 61S along the rotation axis L direction. For this reason, the cooling air entering the outlet cavity 42C from the supply flow path 62S flows to the downstream side of the combustion gas flow along the rotation axis L direction as indicated by an arrow in FIG.
The supply flow paths 62S are arranged at equal intervals in the circumferential direction.

The partition wall flow path 63S is formed through the inside of the inner partition wall portion 61S so as to extend from the inlet cavity 41C toward the bypass space 44C at the upstream end portion of the combustion gas flow in the inner partition wall portion 61S. . That is, the partition channel 63S is a channel that connects the inlet cavity 41C and the bypass space 44C to each other and supplies cooling air from the inlet cavity 41C to the bypass space 44C.
In the present embodiment, the partition flow paths 63S are formed to extend in the radial direction and are arranged at equal intervals in the circumferential direction.

The jumper tube 64S is formed through the inside of the inner partition wall 61S so as to extend from the bypass space 44C toward the rim seal cavity 43C at the downstream end of the combustion gas flow in the inner partition wall 61S. . In other words, the jumper tube 64S forms a flow path that connects the bypass space 44C and the rim seal cavity 43C to each other and supplies cooling air from the bypass space 44C to the rim seal cavity 43C. In the present embodiment, the jumper tube 64S is inclined so as to go radially outward as it goes downstream of the combustion gas flow.
The jumper tubes 64S are arranged at equal intervals in the circumferential direction so as to be positioned between the supply flow paths 62S adjacent in the circumferential direction. In other words, the jumper tubes 64S and the supply flow paths 62S are alternately arranged in the circumferential direction.

  A plug portion 66S is detachably attached to an opening portion of the jumper tube 64S with respect to the rim seal cavity 43C. The plug portion 66S adjusts the flow rate of the cooling air flowing through the jumper tube 64S. That is, the plug portion 66S is formed with a throttle through which cooling air flows, and the flow rate of the cooling air flowing through the jumper tube 64S is adjusted by this throttle.

The protrusion 65S is formed in a substantially cylindrical shape that extends from the downstream end of the combustion gas flow in the inner partition wall 61S along the rotation axis L toward the first stage turbine disk 31R. The protruding portion 65S is located on the radially inner side of the rim seal cavity 43C, and is disposed on the radially outer side of the seal arm 35R of the first stage turbine disk 31R.
And between this protrusion part 65S and the seal arm 35R, the 1st seal | sticker part 67S which interrupts | blocks the flow of the cooling air which flows in into the rim seal cavity 43C from the exit cavity 42C is provided.
The first seal portion 67S is formed so as to extend from the protruding portion 65S toward the seal arm 35R. Specific examples of the first seal portion 67S include a seal member such as a leaf seal, a labyrinth seal, and a brush seal. For example, these seal members may be appropriately combined and are not particularly limited.

A second seal portion 68S and a third seal portion 69S are provided between the inner partition wall portion 61S configured as described above and the connection rotor 38R.
The second seal part 68S is disposed between the opening part of the partition wall flow path 63S that opens to the bypass space 44C and the opening part of the jumper tube 64S. The second seal portion 68S serves as a seal portion that blocks the flow of cooling air that flows into the bypass space 44C from the partition wall channel 63S toward the downstream side of the combustion gas flow.

On the other hand, the third seal portion 69S is disposed at a boundary portion between the bypass space 44C and the outlet cavity 42C located downstream of the opening of the jumper tube 64S that opens to the bypass space 44C. The third seal portion 69S is a seal that blocks the flow of the cooling air that flows into the bypass space 44C from the partition flow path 63S and flows through the second seal portion 68S toward the downstream side of the combustion gas flow. Has become a department.
The second seal portion 68S and the third seal portion 69S are formed to extend from the inner partition wall portion 61S toward the connection rotor 38R. Specific examples of the second seal portion 68S and the third seal portion 69S are the same as those of the first seal portion 67S described above.

  The rim seal cavity 43C is a space surrounded by the first stage turbine disk 31R, the outer partition wall 51S, and the inner partition wall 61S. Cooling air flows into the rim seal cavity 43C through the jumper tube 64S and the first seal portion 67S described above. The rim seal cavity 43C communicates with the gap between the first-stage stationary blade 11S and the first-stage moving blade 21R so that the cooling air flowing into the rim seal cavity 43C can be supplied to the combustion gas flow path.

Furthermore, as shown in FIGS. 2 to 4, the turbine unit 4 of the present embodiment also includes an annular nozzle member 81 </ b> S.
The annular nozzle member 81S imparts a swirling flow that rotates in the same direction as the turbine disk 31R to the cooling air flowing from the inlet cavity 41C toward the outlet cavity 42C. It is provided in the opening that opens.
Specifically, as shown in FIGS. 2 to 7, the annular nozzle member 81 </ b> S is formed in an annular shape centered on the rotational axis L, and an outer ring portion 82 </ b> S formed in an annular shape centered on the rotational axis L. And a plurality of blades arranged between the outer ring portion 82S and the inner ring portion 83S and arranged at equal intervals in the circumferential direction. A shape portion 84S is provided, and the outer ring portion 82S and the inner ring portion 83S are integrally fixed via the airfoil portion 84S. Between the airfoil portions 84S adjacent to each other in the circumferential direction, the TOBI nozzle 85S in which the cross-sectional area of the passage gradually decreases while turning in the rotation direction of the turbine disk 31R from the upstream side to the downstream side of the combustion gas flow. It is defined.

The annular nozzle member 81S is fitted in an annular groove 70S that is recessed from the downstream end face of the combustion gas flow at a position corresponding to the opening of the supply flow path 62S in the inner partition wall 61S.
As described above, the annular nozzle member 81S attached to the inner partition wall 61S has the annular nozzle member 81S when the annular nozzle member 81S and the inner partition wall 61S to which the annular nozzle member 81S is attached are heated by the combustion gas or the like during operation of the gas turbine 1. In order to prevent excessive stress from being generated, the following structure is provided.

That is, the annular nozzle member 81S is configured by a plurality of nozzle division bodies that are divided in the circumferential direction. Note that the annular nozzle member 81S of the present embodiment is configured by two nozzle division bodies 81SA and 81SB divided on a virtual plane (horizontal division plane) including the rotation axis L.
In addition, the annular nozzle member 81S of the present embodiment is particularly configured so that the one airfoil portion 84SC is divided into two nozzle divided bodies 81SA and 81SB, and in particular, the rotation axis L of the one airfoil portion 84SC. Is divided into two nozzle division bodies 81SA and 81SB at a position where the thickness of one airfoil portion 84SC is the largest.

When the annular nozzle member 81S is fitted in the annular groove 70S of the inner partition wall 61S, as shown in FIGS. 5 to 8, two nozzle divided bodies 81SA and 81SB that face the circumferential direction of the annular nozzle member 81S. There is a gap D between the two.
Since the gap D is generated between the two nozzle divided bodies 81SA and 81SB as described above, the annular nozzle member 81S is heated by the operation of the gas turbine 1 and the two nozzle divided bodies 81SA and 81SB are circumferentially moved. Even if it expands, it is possible to prevent the divided surfaces 86S, 86S of the two nozzle divided bodies 81SA, 81SB facing each other in the circumferential direction from coming into contact with each other, or even if they come into contact, the stress generated in each nozzle divided body 81SA, 81SB Can be reduced.

A seal member 91S that fills the gap D is provided in the gap D between the nozzle divided bodies 81SA and 81SB.
If it demonstrates concretely, the sealing member 91S of this embodiment is formed in plate shape with the material (for example, metal material) with high rigidity which is hard to elastically deform, for example.
On the other hand, the two nozzle divided bodies 81SA and 81SB are respectively formed with receiving recesses 87S that are recessed from the divided surfaces 86S of the nozzle divided bodies 81SA and 81SB and receive a part of the seal member 91S. The housing recess 87S is formed so as to extend in the radial direction of the nozzle divided bodies 81SA and 81SB, and opens to the radial inner side and the radial outer side of the annular nozzle member 81S. Furthermore, the housing recess 87S of the present embodiment is formed in a rectangular cross section when viewed from the radial direction of the annular nozzle member 81S.

The plate-shaped seal member 91S is accommodated in both of the two accommodating recesses 87S and 87S so that the thickness direction (the left-right direction in FIG. 7) is along the rotation axis L (the flow direction of the cooling air). Yes. In other words, a part of the seal member 91S is accommodated in each accommodating recess 87S.
The longitudinal dimension l ₁ along the radial direction of the annular nozzle member 81S in the seal member 91S accommodated in this way is set to be substantially equal to the longitudinal dimension l ₂ of the accommodating recess 87S along the radial direction of the annular nozzle member 81S. Has been.

Further, the plate thickness dimension t of the seal member 91S is set smaller than the width dimension w of the housing recess 87S along the rotation axis L.
Furthermore, the height h ₁ of the sealing member 91S in the circumferential direction of the annular nozzle member 81S is larger than at least the depth of one of the accommodation recess 87S h _2, h _3, and each other along the circumferential direction More than the distance h ₄ between the bottom surfaces (bottom portions) of the two housing recesses 87S, 87S facing each other (the depth dimension h ₂ , h _{3 of the} two housing recesses 87S, 87S and the dimension of the gap D) It is set small. Incidentally, the dimension of the gap D, the nozzle divided body by heat 81SA, because it changes by expansion and shrinkage of 81SB, height _{h 1} of the sealing member 91S, the two receiving recesses 87S, the depth of the 87S dimension _h 2, h It is more preferable that the dimension is set to be smaller than the dimension obtained by adding ₃ .

As described above, by setting the dimensions of the seal member 91S (particularly, the plate thickness dimension t and the height dimension h ₁ ), for example, as shown in FIG. 8A, the seal members 91S are accommodated in the two accommodating recesses 87S and 87S. In a state in which the sealed seal member 91S is pressed against one inner surface of the two housing recesses 87S and 87S facing in the same direction (the inner surface of the housing recess 87S positioned on the right side in FIG. 8), One of between the other inner surface of the accommodation recess 87S (inner surface located on the left side in FIG. 8), a gap d ₁ along the rotation axis L direction is generated. Further, gaps d ₂ and d ₃ along the circumferential direction of the annular nozzle member 81S are formed between the seal member 91S and the bottom surface of the housing recess 87S.

Next, general operation of the gas turbine 1 configured as described above will be described.
As shown in FIG. 1, the gas turbine 1 sucks air (air) when the compressor 2 is rotationally driven. The sucked air is compressed by the compressor 2 and sent out toward the combustor 3.
The compressed air flowing into the combustor 3 is mixed with fuel supplied from the outside in the combustor 3. The mixture of air and fuel is combusted in the combustor 3, and hot gas is generated by the combustion heat.
The hot gas generated in the combustor 3 is supplied from the combustor 3 to the downstream turbine unit 4. The turbine unit 4 is rotationally driven by the high-temperature gas, and the rotational driving force is transmitted to the rotary shaft 5. The rotating shaft 5 transmits the rotational driving force extracted in the turbine unit 4 to the compressor 2 and the generator.

Next, a supply method for supplying cooling air to the first stage blade 21R and the rim seal cavity 43C when the operation of the gas turbine 1 is performed as described above will be described.
A part of the air compressed by the compressor 2 is extracted from the compressor 2 and cooled for use as cooling air. Thereafter, the cooling air is supplied from the supply flow path 52S to the inlet cavity 41C as shown in FIGS.
A part of the cooling air supplied to the inlet cavity 41C flows into the supply flow path 62S, and flows into the outlet cavity 42C through the TOBI nozzle 85S (see FIG. 7) of the annular nozzle member 81S. Therefore, during this inflow, a swirl flow rotating in the same direction as the rotating shaft 5 and the first stage turbine disk 31R is given to the cooling air, in other words, the rotating direction of the rotating shaft 5 and the first stage turbine disk 31R. The flow velocity component is given.

Here, as shown in FIGS. 5 to 8, no swirl flow is given to the cooling air that flows into the exit cavity 42 </ b> C from the supply flow path 62 </ b> S through the gap D without passing through the TOBI nozzle 85 </ b> S. Since it is filled with the seal member 91S, the cooling air in the supply flow path 62S does not flow into the outlet cavity 42C through the gap D.
More specifically, the plate-like seal member 91S is formed by the flow of cooling air flowing from the supply flow path 62S toward the annular nozzle member 81S (flow in the direction indicated by the right arrow in FIG. 7). As shown in FIG. 8A, the seal member 91S is pressed against one inner surface of the two housing recesses 87S and 87S by surface contact. Accordingly, the gap D is blocked in the direction of the rotation axis L, so that the cooling air in the supply flow path 62S does not flow through the gap D into the outlet cavity 42C.

As described above, the cooling air in the outlet cavity 42C to which the swirling flow is applied flows into the cooling hole 33R of the first stage turbine disk 31R, flows radially outward, and flows into the axial communication path 36R. To do. Further, the cooling air flowing into the axial communication path 36R flows in the direction of the rotation axis L and flows into the cooling flow path 25R of the first stage blade 21R. The cooling air that has flowed into the cooling flow path 25R cools the blade portion 22R of the first stage moving blade 21R, and is then released, for example, into the combustion gas flow path.
The cooling air in the outlet cavity 42C also flows into the disk flow path 34R of the first stage turbine disk 31R and flows downstream of the combustion gas flow, so that the combustion gas flow is more downstream than the first stage blade 21R. Are also supplied to the moving blades (for example, the two-stage moving blade 211R and the third-stage moving blade 212R shown in FIG. 2).

Furthermore, the cooling air supplied to the inlet cavity 41C also flows into the bypass space 44C via the partition wall flow path 63S.
A part of the cooling air flowing into the bypass space 44C flows toward the upstream side of the combustion gas flow, in other words, toward the compressor 2, and is used for cooling the compressor 2. The remaining cooling air flowing into the bypass space 44C flows toward the second seal portion 68S (downstream of the combustion gas flow).

Furthermore, the cooling air that has passed through the second seal portion 68S is divided into cooling air that flows into the jumper tube 64S and cooling air that flows toward the third seal portion 69S, and the cooling air that flows into the jumper tube 64S is plugged It passes through the restriction of the portion 66S and flows into the rim seal cavity 43C. The cooling air that has passed through the first seal portion 67S flows into the rim seal cavity 43C from the exit cavity 42C.
Then, the cooling air in the rim seal cavity 43C flows out from the gap between the first stage stationary blade 11S and the first stage rotor blade 21R into the combustion gas flow path.

  As described above, according to the configuration of the present embodiment, since the cooling air in the supply flow path 62S is prevented from flowing into the outlet cavity 42C through the gap D, a swirl flow is applied by the TOBI nozzle 85S. The flow velocity component in the rotating direction of the cooling air is not decelerated by the cooling air flowing into the exit cavity 42C through the gap D. That is, it is possible to suppress the swirling flow of the cooling air entering the outlet cavity 42C from the supply flow path 62S from being disturbed by the cooling air flowing into the outlet cavity 42C through the gap D.

  Further, according to the configuration of the present embodiment, the cooling air that has flowed into the bypass space 44C from the inlet cavity 41C is urged to flow into the rim seal cavity 43C by the jumper tube 64S. In other words, it is possible to suppress the cooling air to which the swirl flow is not applied from flowing into the exit cavity 42C from the bypass space 44C. Therefore, it is possible to suppress the swirling flow of the cooling air entering the outlet cavity 42C from the supply flow path 62S from being disturbed by the inflow of the cooling air from the bypass space 44C to the outlet cavity 42C.

  From the above, the circumferential flow velocity component of the cooling air flowing into the outlet cavity 42C in a state where the swirling flow is applied from the supply flow path 62S is equal to the rotational speed at the opening of the cooling hole 33R on the outlet cavity 42C side. Alternatively, since the speed becomes close, the cooling air can flow into the cooling hole 33R while suppressing the generation of energy loss (pumping loss). That is, the performance degradation of the gas turbine 1 can be suppressed.

  Further, according to the configuration of the present embodiment, since the same seal member 91S is accommodated in both of the two accommodating recesses 87S and 87S, the position of the seal member 91S is held, so the seal member 91S is bonded. Even if it is not fixed to the nozzle divided bodies 81SA and 81SB by the above, it is possible to prevent the seal member 91S from dropping out from the gap D to the outlet cavity 42C side due to the flow of cooling air flowing into the gap D from the supply flow path 62S. .

Further, according to the configuration of the present embodiment, between the inner surface of the sealing member 91S and the accommodating recess 87S, for example, as shown in FIG. 8 (a), the gap d ₁ along the rotational axis L _and the annular Since there are gaps d ₂ and d ₃ along the circumferential direction of the nozzle member 81S, for example, as shown in FIG. 8B, the two nozzle division bodies 81SA and 81SB are in the flow direction of the cooling air (FIG. 8B). When the relative position of the two housing recesses 87S and 87S tends to shift in the flow direction of the cooling air, the seal member 91S has two housing recesses 87S and 87S. While maintaining the state accommodated in 87S, it can incline in the flow direction of cooling air with respect to the circumferential direction of the annular nozzle member 81S. Thereby, the shift | offset | difference to the said flow direction of the relative position of two accommodating recessed parts 87S and 87S can be accept | permitted.

Therefore, when the two nozzle division bodies 81SA and 81SB try to shift from each other in the flow direction of the cooling air, it is possible to suppress the stress from being generated in the plate-shaped seal member 91S and the housing recess 87S. Therefore, even if the seal member 91S is formed of a highly rigid material that is not easily elastically deformed, the seal member 91S and the housing recess 87S can be protected.
Further, even if the seal member 91S is inclined as described above, the seal member 91S is held in the two receiving recesses 87S and 87S, so that the seal member 91S is formed of a highly rigid material. However, it is possible to prevent the seal member 91S from flowing into the outlet cavity 42C through the gap D between the two nozzle divided bodies 81SA and 81SB.

Further, in the configuration of the present embodiment, the portion of the one airfoil portion 84SC along the rotation axis L is divided into the two nozzle divided bodies 81SA and 81SB at the portion where the thickness is the thickest. The seal member 91S is provided at the portion where the thickness is the thickest. For this reason, for example, the thickness (plate thickness dimension t) of the seal member 91S along the rotation axis L, the width (width dimension w) of the accommodating recess 87S, and the depth of the accommodating recess 87S along the circumferential direction of the annular nozzle member 81S ( For example, by setting the depth dimensions h ₂ and h ₃ ) to be large, it is possible to secure the maximum area for filling the gap D between the two nozzle divided bodies 81SA and 81SB by the seal member 91S. Therefore, it is possible to more reliably prevent the cooling air from flowing into the outlet cavity 42C through the gap D between the two nozzle divided bodies 81SA and 81SB.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIG. In this embodiment, since only the configuration of the seal member 91S is different from that of the first embodiment, the same components as those in the first embodiment are denoted by the same reference numerals, and the description thereof is omitted.
As shown in FIG. 9, the seal member 91 </ b> S of the present embodiment is formed in a plate shape having a rectangular cross section similar to the first embodiment. The seal member 91S of this embodiment is formed with a pair of protrusions 92S and 92S that bulge in the plate thickness direction of the seal member 91S from the surface of the seal member 91S facing the downstream side in the cooling air flow direction. Yes.

  Each projecting portion 92S, 92S is formed in a semicircular shape when viewed from the radial direction of the annular nozzle member 81S. Specifically, the radial direction of the annular nozzle member 81S (the longitudinal direction of the seal member 91S is shown in FIG. 5 in the left-right direction). The pair of protrusions 92S and 92S are formed so as to include corners at both ends in the height direction (vertical direction in FIG. 9A) of the seal member 91S. Thereby, two corners located on the downstream side in the flow direction of the cooling air in the sealing member 91S are rounded.

  As described above, in the configuration of the present embodiment, for example, as shown in FIG. 9A, when the relative positions of the two housing recesses 87S and 87S along the flow direction of the cooling air coincide, Due to the flow of cooling air flowing into the gap D from the inside of the passage 62S (the flow toward the right in FIG. 9), the tip of each rounded projection 92S is pressed against one inner surface of the two housing recesses 87S, 87S. . Since the protrusions 92S are brought into close contact with the one inner surface in this way, the gap D is blocked in the direction of the rotation axis L, so that the cooling air in the supply flow path 62S is the same as in the first embodiment. Does not flow through the gap D into the outlet cavity 42C.

On the other hand, as shown in FIGS. 9B and 9C, for example, the two housing recesses 87S and 87S are shifted from each other in the flow direction of the cooling air, and the seal member 91S is the first embodiment (see FIG. 8B). ), The at least one protrusion 92S is pressed against one inner surface of the housing recess 87S.
More specifically, as shown in FIG. 9B, when the displacement between the two housing recesses 87S and 87S is large, only one projection 92S (upper projection 92S in the illustrated example) is accommodated. It is pressed against one inner surface of the recess 87S. As shown in FIG. 9C, when the displacement between the two housing recesses 87S and 87S is small, both the protrusions 92S are pressed against one inner surface of the two housing recesses 87S.

That is, according to the configuration of the present embodiment, even if the seal member 91S is inclined due to the displacement of the two housing recesses 87S, 87S, for example, as in the first embodiment (FIG. 8B), the flow of cooling air Compared with the case where the sharp corner of the seal member 91S located on the downstream side in the direction hits one inner surface of the housing recess 87S, the corner rounded by the protrusion 92S and one of the housing recess 87S Adhesion with the inner surface is improved. Therefore, the sealing member 91S is formed in a plate shape as a whole, and even if the two receiving recesses 87S and 87S are displaced from each other in the flow direction of the cooling air, the cooling air has a gap D between the two nozzle divided bodies 81SA and 81SB. It is possible to more reliably prevent the air from flowing into the outlet cavity 42C.
In particular, in the configuration of the present embodiment, since the rounded protrusions 92S are formed at the two corners of the seal member 91S located on the downstream side in the cooling air flow direction, the two housing recesses 87S, When the seal member 91S is inclined due to the deviation of 87S, both the two protrusions 92S can be brought into contact with each other, so that the cooling air can be further reliably prevented from flowing into the outlet cavity 42C through the gap D. be able to.
And in the structure of this embodiment, there exists an effect similar to 1st embodiment besides the effect mentioned above.

In the configuration of the second embodiment, the two corners of the seal member 91S located on the downstream side in the cooling air flow direction are rounded. However, the present invention is not limited to this, and the pair of protrusions 92S, These two corners may be rounded without using 92S. Furthermore, only one of the two corners of the seal member 91S located on the downstream side in the flow direction of the cooling air may be rounded.
Further, for example, two corners of the seal member 91S located on the upstream side in the flow direction of the cooling air may be rounded.
Furthermore, in the configuration of the first and second embodiments described above, the seal member 91S is formed of a highly rigid material that is not easily elastically deformed. However, the seal member 91S may be configured of an elastic body that can be elastically deformed, for example.

[Third to fifth embodiments]
Next, third to fifth embodiments of the present invention will be described with reference to FIGS. In these embodiments, only the configuration of the seal member 91S is different from that of the first embodiment. Therefore, the same components as those in the first embodiment are denoted by the same reference numerals, and the description thereof is omitted.
As shown in FIG. 10, the seal member 91 </ b> S of the third embodiment is configured by an elastic body that can be elastically deformed, such as rubber, for example, and the radial direction of the annular nozzle member 81 </ b> S ). In addition, the sealing member 91S in the illustrated example is formed in a circular shape or an elliptical shape in a cross section (the cross section shown in FIG. 10) orthogonal to the radial direction of the annular nozzle member 81S. You may form in the same plate shape as embodiment.

Further, as shown in FIG. 11, the seal member 91S of the fourth embodiment is formed in a C shape with a cross section (cross section shown in FIG. 11) orthogonal to the radial direction of the annular nozzle member 81S.
Furthermore, as shown in FIG. 12, the seal member 91S of the fifth embodiment is formed in an E shape with a cross section (cross section shown in FIG. 12) orthogonal to the radial direction of the annular nozzle member 81S.
The seal member 91S shown in FIGS. 11 and 12 is formed by bending a plate-like member made of, for example, a metal material, and has a spring property by a shape of a C-shaped cross section or an E-shaped cross section. It is an elastic body that can be elastically deformed. That is, the seal member 91S shown in FIGS. 11 and 12 constitutes a so-called C seal or E seal.
As described above, the seal member 91S formed in a C shape or an E shape has the opening 93S of the seal member 91S in the cross section shown in FIGS. 11 and 12 upstream in the cooling air flow direction (in FIGS. 11 and 12). It is accommodated in the two accommodating recesses 87S and 87S so as to open to the left side).

  10-12 are both housed in the two housing recesses 87S, 87S, and are compressed (elastically deformed) in the circumferential direction (vertical direction in FIGS. 10-12) of the annular nozzle member 81S. ) In such a state that it is sandwiched between the two nozzle divided bodies 81SA and 81SB. In addition, although these sealing members 91S may be accommodated in each accommodation recessed part 87S and 87S in the state compressed and deformed also in the rotation axis L direction (left-right direction in FIGS. 10-12), it is not restricted to this.

According to the configurations of the third to fifth embodiments, the same effects as those of the first embodiment can be obtained.
Furthermore, according to the configuration of the third to fifth embodiments, since the sealing member 91S is in close contact with the bottom surfaces of the two receiving recesses 87S and 87S, the cooling air in the supply flow path 62S is provided with two nozzles. It is possible to reliably prevent the air from flowing into the exit cavity 42C through the gap D between the divided bodies 81SA and 81SB. In addition, since the seal member 91S is an elastic body that can be elastically deformed, it is possible to follow the dimensional change of the gap D due to the thermal deformation (expansion and contraction) of the nozzle divided bodies 81SA and 81SB and prevent the adhesion from being lowered.
Further, according to the configuration of the fourth and fifth embodiments, since the seal member 91S is arranged so that the opening 93S of the seal member 91S opens upstream in the flow direction of the cooling air, the supply flow path 62S. Since the flow of the cooling air entering the gap D from the inside flows into the inside of the seal member 91S, the seal member 91S can be pressed against the inner surface of the housing recess 87S. Therefore, the adhesion between the sealing member 91S and the inner surface of the housing recess 87S is improved, and the cooling air is more reliably prevented from flowing into the outlet cavity 42C through the gap D between the two nozzle divided bodies 81SA and 81SB. Can do.

In addition, when the sealing member 91S is configured by an elastic body as in the third to fifth embodiments, for example, the sealing member 91S may be fixed to only one of the two nozzle divided bodies 81SA and 81SB by adhesion or the like. For example, even if the sealing member 91S is compressed and deformed (elastically deformed) without being fixed, the sealing member 91S can be sealed by the elastic force of the sealing member 91S only by being inserted into the gap D between the two nozzle divided bodies 81SA and 81SB. It is also possible to hold the member 91S in the gap D between the two nozzle divided bodies 81SA and 81SB.
Accordingly, the housing recess 87S that houses a part of the seal member 91S may be formed only in one nozzle division 81SA as shown in FIGS. 13 and 14, for example, as shown in FIG. It does not have to be done.

Here, the seal member 91S shown in FIG. 13 is a so-called brush seal, for example, a base 94S formed in a plate shape, and a brush made of many needles or hairs planted on the base 94S. The main body 95S is provided.
In this configuration, the base 94S of the seal member 91S is housed and fixed by being fitted into the housing recess 87S formed in the one nozzle divided body 81SA. And in this accommodation state, the brush main-body part 95S is extended and pressed toward the division | segmentation surface 86S of the other nozzle division body 81SB from the base 94S. In this pressed state, the brush body 95S is elastically deformed so as to be bent, for example.
According to the configuration shown in FIG. 13, similarly to the third to fifth embodiments described above, the flow of cooling air flows through the gap D by the elastic force of the brush main body portion 95S pressed against the other nozzle divided body 81SB. Therefore, the cooling air in the supply flow path 62S can be reliably prevented from passing through the gap D and flowing into the outlet cavity 42C.

14 is a so-called leaf seal, and includes, for example, a base 94S formed in a plate shape and a plurality of sheet-like bodies 96S planted on the base 94S. Yes.
In this configuration, the base 94S of the seal member 91S is housed and fixed by being fitted into the housing recess 87S of the one nozzle divided body 81SA. In this accommodated state, the plurality of sheet-like bodies 96S are arranged in the cooling air flow direction (left-right direction in FIG. 14). The leading ends of the plurality of sheet-like bodies 96S in the protruding direction are pressed against the dividing surface 86S of the other nozzle divided body 81SB and elastically deformed so as to bend. In addition, it is preferable that the plurality of sheet-like bodies 96S bend and be deformed so that the front ends thereof face upstream in the flow direction of the cooling air.
According to the configuration shown in FIG. 14, the same effects as in the case of FIG. Further, the plurality of sheet-like bodies 96S are bent and deformed so that the leading ends thereof are directed upstream in the flow direction of the cooling air, so that the leading end of the sheet-like body 96S and the other end are caused by the flow of cooling air flowing into the gap D. It is possible to reliably prevent a gap from being formed between the nozzle division body 81SB and the division surface 86S.

The sealing member 91S shown in FIG. 15 is curved and deformed so that an intermediate portion of the plate-like member extending in the cooling air flow direction swells in the circumferential direction (upward in FIG. 15) of the annular nozzle member 81S. Accordingly, it can be elastically deformed at least in the circumferential direction of the annular nozzle member 81S.
In this configuration, for example, one end in the extending direction of the seal member 91S may be fixed to the dividing surface 86S of the other nozzle divided body 81SB by adhesion or the like, or in the middle in the extending direction of the seal member 91S. The portion may be fixed to the dividing surface 86S of one nozzle divided body 81SA. In this configuration, for example, the seal member 91S is not fixed to the nozzle divided bodies 81SA and 81SB, but the seal member 91S is compressed and deformed (elastically deformed), and the gap D between the two nozzle divided bodies 81SA and 81SB is formed. By inserting, the sealing member 91S may be held in the gap D by the elastic force of the sealing member 91S.

According to the configuration shown in FIG. 15, as in the case of FIGS. 13 and 14, the seal member 91 </ b> S comes into close contact with the dividing surface 86 </ b> S of the two nozzle divided bodies 81 </ b> SA and 81 </ b> SB by its elastic force. Can be reliably prevented from flowing through the gap D between the two nozzle divided bodies 81SA and 81SB and flowing into the outlet cavity 42C.
Note that the seal member 91S shown in FIG. 15 is not limited to being provided on the dividing surface 86S without the accommodating recess 87S, and is fitted into the accommodating recess 87S provided in at least one of the nozzle divided bodies 81SA and 81SB, for example. It may be provided.

Although the details of the present invention have been described above, the present invention is not limited to the above-described embodiments, and various modifications can be made without departing from the spirit of the present invention.
For example, the annular nozzle member 81S of all the embodiments described above is formed so as to allow the cooling air to pass in the direction of the rotation axis L, but is not limited thereto, and enters the outlet cavity 42C from the supply flow path 62S. It may be appropriately formed according to the direction of the cooling air flow.

  More specifically, for example, when the opening of the supply flow path 62S with respect to the outlet cavity 42C opens to the inner side in the radial direction of the inner partition wall 61S, the cooling air entering the outlet cavity 42C from the supply flow path 62S also It will flow radially inward. In this case, the annular nozzle member 81S may be formed so as to allow the cooling air to pass radially inward and to impart a swirl flow that rotates in the same direction as the first stage turbine disk 31R. Even with such a configuration, it is possible to provide the seal member 91S as in all the embodiments described above (configurations shown in FIGS. 8 to 15).

The housing recess 87S that is formed in the nozzle division bodies 81SA and 81SB and accommodates the seal member 91S is not limited to be formed in a rectangular cross section, and is formed so that at least a part of the seal member 91S can be accommodated and held. If it is, it may be formed in an arbitrary cross-sectional shape.
Furthermore, the annular nozzle member 81S is not limited to being constituted by the two nozzle division bodies 81SA and 81SB, but may be constituted by three or more nozzle division bodies.
In the gas turbine 1 according to the above embodiment, the rim seal cavity 43C, the bypass space 44C, the partition wall flow path 63S, and the jumper tube 64S are formed.

DESCRIPTION OF SYMBOLS 1 ... Gas turbine, 2 ... Compressor (compression part), 3 ... Combustor (combustion part), 11S ... 1st stage stationary blade (stator blade), 21R ... 1st stage | paragraph moving blade (blade), 25R ... Cooling flow path, 31R ... 1-stage turbine disk (turbine disk), 33R ... Cooling hole, 41C ... Inlet cavity (first inlet space), 42C ... Outlet cavity (second inlet space), 61S ... Inner partition wall (tubular partition), 62S ... Supply flow path, 81S ... annular nozzle member, 81SA, 81SB ... nozzle divided body, 84S ... airfoil part, 84SC ... one airfoil part, 85S ... TOBI nozzle, 86S ... split surface, 87S ... accommodating recess, 91S ... Seal member, 92S ... projection, D ... gap, L ... rotation axis (axis)

Claims (8)

A plurality of rotor blades are attached to the outer periphery side by side in the circumferential direction, and a turbine disk that is rotatably supported around an axis,
A cooling hole that is formed so as to penetrate the inside of the turbine disk, and that supplies a cooling medium to a cooling flow path inside the rotor blade;
A cylindrical partition section that is formed in a cylindrical shape centered on the axis, and that defines a first inlet space to which the cooling medium is supplied from the outside, and a second inlet space that communicates with the cooling hole;
A supply flow path that extends from the first inlet space toward the second inlet space and supplies the cooling medium from the first inlet space to the second inlet space;
The axis is formed in an annular shape centering on the axis, and is provided in an opening on the second inlet space side in the supply flow path, and the axis extends from the first inlet space toward the second inlet space. An annular nozzle member that imparts a swirling flow that rotates in the same direction as the turbine disk to the cooling medium flowing in a direction ;
The annular nozzle member is constituted by a plurality of nozzle division bodies that are divided in the circumferential direction,
A cooling structure for a turbine, wherein a seal member is provided in a gap between two nozzle division bodies adjacent in the circumferential direction so as to fill the gap in the axial direction .   The at least one nozzle divided body of the two nozzle divided bodies is recessed from the dividing surface of the one nozzle divided body that defines the gap together with the other nozzle divided body, and accommodates a part of the seal portion. The turbine cooling structure according to claim 1, wherein an accommodation recess is formed. The housing recess is formed in the two nozzle divided bodies,
The turbine cooling structure according to claim 2, wherein the seal member is housed in the two housing recesses. The seal member is formed in a plate shape, and is housed in the two housing recesses such that the thickness direction of the seal member is along the flow direction of the cooling medium flowing into the gap from the supply flow path,
The width dimension of the accommodating recess along the flow direction of the cooling medium is set larger than the plate thickness dimension of the seal member,
The distance between the bottoms of the two housing recesses facing each other along the circumferential direction is set to be larger than the height dimension of the seal member along the circumferential direction. Turbine cooling structure.   5. The turbine cooling structure according to claim 4, wherein at least one of corner portions located on the downstream side in the flow direction of the cooling medium of the sealing member formed in a plate shape is rounded. .   The turbine cooling structure according to any one of claims 1 to 5, wherein the seal member is formed of an elastic body that is elastically deformable. The annular nozzle member includes a plurality of airfoils arranged in the circumferential direction to impart the swirl flow to the cooling medium;
One airfoil is formed by dividing the two nozzle divided bodies,
The one airfoil part is divided in a portion where the thickness of the one airfoil part along the flow direction of the cooling medium flowing into the gap from the supply flow path is the thickest. The turbine cooling structure according to any one of claims 1 to 6. A compression unit that sucks and compresses air, a combustion unit that generates a combustion gas by burning a mixture of compressed air and fuel supplied from the outside, and a rotational driving force is extracted from the generated combustion gas And a turbine part
A gas turbine, wherein the turbine cooling structure according to any one of claims 1 to 7 is provided in the turbine section.

Images