JP2001012204A - Gas turbine blades - Google Patents

Abstract

(57) [Summary] A gas turbine blade according to the present invention maintains a high persistence of a film extending long toward the downstream side of a cooling medium,
A gas turbine blade with further increased diffusivity is provided. In a gas turbine blade according to the present invention, a film discharge flow (32) in which a momentum (momentum) of a cooling medium (CA) is increased at a center portion of a discharge port (26), and a momentum of a cooling medium (CA) flows at an outer portion thereof. The film 30 was formed in a horseshoe shape having a curved surface through which the membrane ejection flow 30 with reduced (momentum) flowed out.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine blade, and more particularly to a gas turbine blade that effectively cools a blade surface with a film.

[0002]

2. Description of the Related Art A gas turbine plant includes an air compressor,
Equipped with a gas turbine combustor and a gas turbine, the air (air) sucked in by an air compressor is compressed to a high pressure, and the high-pressure air is supplied to a gas turbine combustor together with fuel to generate combustion gas. The combustion gas is supplied to a gas turbine to perform expansion work and generate power.

In a gas turbine plant having such a configuration, it is known that the higher the temperature of the combustion gas supplied from the gas turbine combustor to the gas turbine increases in order to improve the plant thermal efficiency. I have.

[0004] However, in order to raise the temperature of the combustion gas, it is necessary to take measures to increase the temperature of the first and second stage gas turbine stationary blades and gas turbine rotor blades housed in the gas turbine.

[0005] One of the measures against the high temperature of gas turbine blades is as follows.
There is known a so-called film cooling technique in which a cooling medium flows on a blade surface in the form of a film.

FIGS. 16 to 26 show an example in which a film cooling technique is applied to a gas turbine rotor blade. As shown in FIG. 16, the gas turbine rotor blade includes a blade effective portion 1 and a blade implant portion 2. As shown in FIG. 17 and FIG. 18, a plurality of independent cooling passages 3 are sequentially provided from the leading edge side of the blade to the trailing edge side of the blade.
a, 3b, 3c are formed, and these cooling passages 3a, 3c are formed.
The inlet sides of b and 3c are connected to a cooling passage provided in a turbine shaft (not shown).

The cooling medium guided to the cooling passages 3a, 3b, 3c passes through the blade implant portion 2 and performs convection cooling while flowing into the blade effective portion 1. The cooling medium guided to the cooling passages 3a and 3b on the blade leading edge side and the blade center part side blows out as a film film provided on the leading edge 4, the belly side 5, the back side 6 and the blade tip part 8. To flow out of the wings. Further, the cooling medium guided to the cooling passage 3 c on the trailing edge side of the blade is supplied to the convective cooling outlet 10 provided at the trailing edge 9.
To flow out of the wings.

The vent 8 provided through the ventral side 5 and the back side 6 has a circular cross section.
The ejection center line 12 of the ejection port 8 is inclined in a direction toward the downstream side of the gas turbine driving gas (main flow) 11 flowing along each of the ventral side 5 and the back side 6 as shown in FIGS. Let me. When the cooling medium 13 flowing out from the outlet 8 is mixed with the gas turbine driving gas (main stream), the cooling medium 13 cools the effective blade portion 11 while spreading the surface of the effective blade portion 1 like a film.

[0009] The position and orientation of the outlet 8 are as follows.
A direction perpendicular to the flow direction of the gas turbine driving gas (main flow) 11 shown in FIGS. 21 and 22, for example, so that the cooling medium flows over a wider area and has a uniform film thickness when flowing on the blade surface. There is an example in which a plurality of rows are formed, and the outlet 8 located on the upstream side and the outlet 8 located on the downstream side shown in FIG. 23 are alternately arranged.
Further, in another example, the outlet 8 is branched,
As shown in FIGS. 4 and 25, the outlet side of the outlet 8 is formed as an enlarged opening 14, or as shown in FIG. 26, the outlet side of the outlet 8 is formed as a step-shaped enlarged opening 15. (JP-A-2-28203, JP-A-7-158403).

[0010]

The cooling technique shown in FIGS. 17 to 23 has some disadvantages and disadvantages.

First, when the ejection port 8 is formed in a circular shape, the cooling medium 13 ejected from the ejection port 8 has a large momentum (momentum) of the ejection flow, and has a film-film-like sustainability that extends long toward the downstream side. However, the gas turbine driving gas (main stream) 11 flows between the blade wall and the film film, and the film film-like winding phenomenon occurs. This makes it difficult to obtain a greater cooling effect.

In the cooling technique shown in FIGS. 24 to 26, if the outlet 8 is gradually or stepwise expanded to widen the outflow angle of the cooling medium, the outflow velocity decreases. As a result, the momentum (momentum) of the jet flow becomes small, the persistence of the film extending long toward the downstream side becomes low, and a greater cooling effect cannot be obtained.

In recent gas turbine plants, the temperature of the combustion gas at the gas turbine inlet is further increased, and as the output of the gas turbine is further increased, the improvement of a new cooling technique for realizing the increased output is required. Have been.

The present invention has been made on the basis of such background art, and further maintains the continuity of a film extending long toward the downstream side of the cooling medium at a higher level. It is an object of the present invention to provide a gas turbine blade that maintains the diffusivity of a film film that spreads further higher.

[0015]

In order to achieve the above object, a gas turbine blade according to the present invention discharges a cooling medium in a film form along a surface of an effective blade portion as described in claim 1. In a gas turbine blade provided with an ejection port for causing
The outlet is formed in a horseshoe shape having a curved surface through which a film jet flow having a large momentum of the cooling medium flows out at a center portion thereof and a film jet flow having a small momentum of the cooling medium flows out at an outer portion thereof. Things.

In order to achieve the above object, the gas turbine blade according to the present invention, as described in claim 2, is characterized in that the horseshoe-shaped outlet has a curved center position of the curved surface on the downstream side of the outlet. It is set.

In order to achieve the above object, the gas turbine blade according to the present invention, as described in claim 3, is characterized in that the horseshoe-shaped outlet has a curvature center position of a curved surface on the upstream side of the outlet. It is set.

In the gas turbine blade according to the present invention, in order to achieve the above object, as set forth in claim 4, the horseshoe-shaped outlet is provided at the center of the outlet connecting the inlet and the outlet. The line has an upward inclination angle in a direction toward the downstream side where the gas turbine driving gas flows.

In order to achieve the above object, the gas turbine blade according to the present invention is provided with a blow-off port through which the cooling medium flows out in a film form along the surface of the blade effective portion. In the gas turbine blade, the outlet is divided into a first outlet and a second outlet and arranged in parallel with each other, and the first outlet is provided with a film in which the momentum of the cooling medium is increased at a central portion thereof. A film in which the jet flow is discharged, and the outer surface of the film is formed in a horseshoe shape having a curved surface on which the momentum of the cooling medium is reduced to allow the jet flow to flow, while the second jet port is formed with a film in which the momentum of the cooling medium is increased. It is formed in one of a circular cross section and an elliptical cross section through which a jet flow flows out.

In order to achieve the above object, the gas turbine blade according to the present invention, as described in claim 6, is provided with a blow-off port through which the cooling medium flows out in a film form along the surface of the blade effective portion. In the gas turbine blade, the jet port is divided into a first jet port and a second jet port, and the first jet port is arranged in the middle of the second jet port and on both outer sides thereof, A horseshoe-like shape having a curved surface through which the first jet outlet flows out a membrane jet flow with a large momentum of the cooling medium at a central portion thereof, and flows out a membrane jet flow with a small momentum of the cooling medium at an outer portion thereof. On the other hand, the second outlet is formed in one of a circular cross section and an elliptical cross section through which a film jet flow having a large momentum of the cooling medium flows out. It is obtained by forming in.

According to a seventh aspect of the present invention, a gas turbine blade according to the present invention is provided with a discharge port through which a cooling medium flows out in a film along the surface of the effective blade portion. In the gas turbine blade, the outlet is provided with a curved surface through which a film jet flow having a large momentum of the cooling medium flows out at a central portion thereof and a film jet flow having a small momentum of the cooling medium flows out at an outer portion thereof. In addition to being formed in a horseshoe shape, the center line of the passage connecting the inlet part and the outlet part of the outlet is inclined upward in the direction toward the downstream side where the gas turbine driving gas flows, and the center line is connected to the outlet part. The gas turbine driving gas flow direction side diffusion portion is formed with an inclination angle in a direction toward the downstream side where the gas turbine driving gas flows again. That.

In order to achieve the above object, the gas turbine blade according to the present invention, as described in claim 8, is provided with a blow-off port through which the cooling medium flows out in a film form along the surface of the blade effective portion. In the gas turbine blade, the outlet is provided with a curved surface through which a film jet flow having a large momentum of the cooling medium flows out at a central portion thereof and a film jet flow having a small momentum of the cooling medium flows out at an outer portion thereof. While forming a horseshoe shape, the center line of the passage connecting the inlet part and the outlet part of the outlet is inclined upward in the direction toward the downstream side where the gas turbine driving gas flows, and the center line is further connected to the outlet. A gas turbine driving gas flow reverse-direction diffusion portion is formed by giving an inclination angle in the direction toward the upstream side where the gas turbine driving gas flows again at the portion A.

According to a ninth aspect of the present invention, a gas turbine blade according to the present invention is provided with a discharge port through which a cooling medium flows out in a film along the surface of the blade effective portion. In the gas turbine blade, the outlet is provided with a curved surface through which a film jet flow having a large momentum of the cooling medium flows out at a central portion thereof and a film jet flow having a small momentum of the cooling medium flows out at an outer portion thereof. While forming a horseshoe shape, the center line of the passage connecting the inlet part and the outlet part of the outlet is inclined upward in the direction toward the downstream side where the gas turbine driving gas flows, and the center line is further connected to the outlet. The inclination angles in the direction toward the downstream side where the gas turbine driving gas flows again and the direction toward the upstream side where the gas turbine driving gas flows again at the portion The is obtained by forming a gas turbine driving gas flow direction side diffusion section and a gas turbine driving gas flow reverse side diffusion section imparted.

In order to achieve the above object, the gas turbine blade according to the present invention is provided with an outlet for discharging the cooling medium in a film form along the surface of the blade effective portion. In the gas turbine blade, the outlet of the outlet is made common and the outlet is made plural, and the common inlet and the plurality of outlets are connected by a plurality of passages, and the outlet of the outlet is The film is formed in a horseshoe shape having a curved surface at a central portion thereof for allowing a film jet flow having a large momentum of the cooling medium to flow out, and an outer portion thereof for flowing the film jet flow having a small momentum of the cooling medium to flow out.

In order to achieve the above object, the gas turbine blade according to the present invention, as described in claim 11, is provided with a discharge port for discharging a cooling medium in a film form along the surface of the blade effective portion. In the gas turbine blade, the inlet of the outlet is formed in a circular cross section, and the outlet of the outlet is provided with a curved surface at a central portion thereof for allowing a film jet flow with a reduced momentum of the cooling medium to flow out. And a passage connecting the inlet portion and the outlet portion is formed in an expanded shape.

[0026]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of a gas turbine blade according to the present invention will be described with reference to the drawings and reference numerals attached to the drawings. The gas turbine blade will be described by taking a gas turbine blade as an example.

FIG. 1 shows a gas turbine blade according to the present invention,
1 is a schematic perspective view showing a first embodiment taken as an example of a gas turbine blade.

The gas turbine rotor blade according to the present embodiment is provided with a blade effective portion 20 and a blade implant portion 21 implanted on a turbine shaft (not shown).

The wing effective portion 20 and the wing implanting portion 21
As shown in FIGS. 17 and 18, a plurality of independent cooling passages are formed in order from the blade leading edge side to the blade trailing edge side, and the cooling passages whose inlet sides are provided on the turbine shaft are formed. It is connected to the.

The cooling medium guided to the cooling passage passes through the blade implant portion 21 and performs convection cooling while flowing into the blade effective portion 20. The cooling medium guided to the cooling passages on the wing leading edge side and the wing central part side blows out from the bleeding ports 26, which are provided on the leading edge 22, the ventral side 23, the back side 24, and the wing tip portion 25, respectively, and blow out. Through the wings. Further, the cooling medium guided to the cooling passage on the trailing edge side of the blade is supplied to a convection cooling jet port 28 provided at the trailing edge 27.
To flow out of the wings.

FIG. 2 is a partially enlarged view showing a blow-out port 26 formed in the ventral side 23, the back side 24, and the wing tip portion 25 of the wing effective portion 20 shown in FIG.

In the gas turbine rotor blade according to the present embodiment, the jet port 26 has a film jet flow in which the momentum (momentum) of the cooling medium CA is increased by increasing the flow velocity at the central portion 29 having the smallest opening area of the gap t. 32 is formed in a horseshoe shape having a curved surface through which the membrane ejection flow 30 having a relatively large opening area at the outer portion 31 and a reduced flow velocity to reduce the momentum (momentum) of the cooling medium CA is discharged. It was done.

As described above, in the present embodiment, the outlet 26 is formed in a horseshoe shape having a curved surface, and the central portion 2 is formed.
9, the film ejection flow 32 in which the flow velocity was increased to increase the momentum of the cooling medium CA and the film ejection flow 30 in which the flow velocity was decreased in the outer portion 31 to decrease the momentum of the cooling medium CA were combined. Part 29
, The film-film-like distance extending long toward the downstream side of the cooling medium CA can be maintained for a long time.
As a result, it is possible to promote the diffusibility of the film film spreading toward the downstream side of the cooling medium CA.

Therefore, according to this embodiment, since the film-like cooling by the cooling medium CA is further improved, it is possible to easily realize a high temperature of the gas turbine plant.

FIG. 3 is a schematic developed plan view showing a second embodiment of the gas turbine blade according to the present invention. Note that the same reference numerals are given to portions corresponding to the first embodiment.

In the gas turbine blade according to the present embodiment, the discharge port 26 is formed on each of the ventral side 23, the back side 24, and the blade tip part 25 of the blade effective portion 20 in contact with the gas turbine driving gas (main flow) 33. In the same manner as in the first embodiment, the film ejection flow 32 having a larger momentum (momentum) of the cooling medium CA flows out at the central portion 29 having the smallest gap t, and the outer portion 31 of the cooling medium CA has the outer portion 31. The momentum (momentum) is formed in a horseshoe shape having a curved surface for allowing the membrane jet flow 30 to flow out, and the curvature center position P of the horseshoe-shaped curved surface in the central portion 29 on the upstream side facing the gas turbine driving gas is determined. This is set at a position on the downstream side of the gas turbine driving gas 33.

As described above, in the present embodiment, the ejection port 26 is formed in a horseshoe shape, and the center of curvature P of the horseshoe-shaped curved surface is set at a position downstream of the gas turbine driving gas 33.
The film ejection flow 32 having a larger momentum of the cooling medium CA in the central portion 29 is caused to flow out, and the film ejection flow 30 having a smaller momentum of the cooling medium CA in the outer portion 31 is caused to flow out toward the downstream side of the cooling medium CA. As a result, the film-film-like distance extending toward the downstream side of the cooling medium CA is further promoted, so that higher film-film-like cooling can be exhibited. In the present embodiment, the outlet 26 is formed in a horseshoe shape having a curved surface, and the curvature center position P is set on the downstream side of the gas turbine driving gas 33. However, the present invention is not limited to this example. As shown in (5), the curvature center position P may be set at a position on the upstream side of the gas turbine driving gas 33. The film ejection flow 30 in which the momentum of the cooling medium CA flowing out of the outer portion 31 of the ejection port 26 is reduced and collides with the gas turbine driving gas 33 to disturb the flow is effective in increasing the diffusivity.

FIG. 5 is a schematic developed plan view showing a third embodiment of the gas turbine blade according to the present invention. Note that the same reference numerals are given to portions corresponding to the first embodiment.

In the gas turbine blade according to the present embodiment, the jet port 26 has a film jet flow 32 in which the momentum of the cooling medium CA is increased at the central portion 29 having the smallest gap t.
Is formed into a horseshoe shape having a curved surface through which an outer portion 31 of the membrane 30 has a curved surface through which the membrane ejection flow 30 with reduced momentum of the cooling medium CA flows out.
The outlet center line 34 of the passage 39 connecting the nozzle 7 and its outlet 38 intersects with the flow direction of the gas turbine driving gas 33 at an inclining angle toward the downstream side.

As described above, in this embodiment, the outlet 26 is formed in a horseshoe shape, and the inlet 37 and the outlet 3 are formed.
8 is intersected with the flow direction of the gas turbine drive gas 33 at an upward inclination angle toward the downstream side, so that the film ejection flow 32 in which the momentum of the cooling medium CA is increased. In addition, it is possible to diffuse the film ejection flow 30 in which the momentum of the cooling medium CA is reduced in all directions, thereby exhibiting even higher film film cooling.

FIG. 6 is a schematic developed plan view showing a fourth embodiment of the gas turbine blade according to the present invention. Note that the same reference numerals are given to portions corresponding to the first embodiment.

The gas turbine blade according to the present embodiment has a ventral side 2 of the blade effective portion 20 which is in contact with the gas turbine driving gas 33.
3. Each of the back side 24 and the wing tip 25 has a first
And the second discharge port 36 are arranged in parallel.

As in the case of the first embodiment, the first outlet 35 is provided with the cooling medium C at the central portion 29 having the smallest gap t.
A is formed in a horseshoe shape having a curved surface through which the membrane ejection flow 32 having a larger momentum A flows out, and the membrane ejection flow 30 having a smaller momentum of the cooling medium CA flows out at an outer portion 31 thereof.

The second ejection port 36 is formed in a circular or elliptical cross section through which the film ejection flow 32 having a large momentum of the cooling medium CA flows out.

As described above, in the present embodiment, the central portion 2
9, the membrane ejection flow 32 having the increased momentum of the cooling medium CA is discharged, and the cooling medium C
A combination of a first ejection port 35 for allowing the film ejection flow 30 with a reduced momentum of A to flow out and a second ejection port 36 for allowing the film ejection flow 32 with a large momentum of the cooling medium CA to flow out provides cooling performance. Since the reinforcement is achieved, it is possible to exhibit a still higher film film cooling. In the present embodiment, the first ejection port 35 and the second ejection port 36 are arranged in parallel, and the ventral side 23, the back side 24, and the wing tip section 2 of the wing effective portion 20 are arranged.
5, but is not limited to this example. For example, as shown in FIG.
May be formed and arranged. This is effective in further strengthening film film cooling.

FIGS. 8 and 9 are schematic views showing a fifth embodiment of the gas turbine blade according to the present invention. FIG.
Is a plan view extracted and developed by extracting a part of the wing effective portion,
FIG. 9 is a cross-sectional view taken along the line AA of FIG. In addition, parts corresponding to the first embodiment are denoted by the same reference numerals.

The gas turbine blade according to the present embodiment has a ventral side 2 of the blade effective portion 20 in contact with the gas turbine driving gas 33.
3. In the same manner as in the first embodiment, the jet port 26 provided in each of the back side 24 and the wing tip portion 25 flows out the membrane jet stream 32 in which the momentum of the cooling medium CA is increased at the central portion 29 having the smallest gap t. The outer portion 31 is formed into a horseshoe shape having a curved surface through which the film ejection flow 30 having a reduced momentum of the cooling medium CA is reduced, as shown in FIG. 9, and as shown in FIG. The center line 40 of the passage 39 connecting to the outlet 38 is formed so as to have an upward inclination angle in a direction toward the downstream side of the gas turbine driving gas 33.

Further, the gas turbine blade according to the present embodiment is provided at a portion of the outlet portion 38 of the passage 39 which is further away from the gas turbine driving gas 33, in a direction partially further away from the gas turbine driving gas 33. Gas turbine drive gas flow direction side diffusion portion 41 having an inclination angle toward it
This is an enlarged view of the passage 39 provided with.

As described above, in the present embodiment, the gas turbine driving gas flow direction side diffusion portion 41 having a partial inclination angle at the outlet portion 38 of the ejection port 26 is provided and the passage 39 is provided.
, The diffusivity of the cooling medium CA is reduced
The position can be further improved.

Therefore, according to the present embodiment, the cooling medium flowing out of the outlet portion 38 of the ejection port 26 is prevented from being caught by the gas turbine driving gas 33, and the surface of the blade effective portion 20 can be uniformly cooled. it can.

FIGS. 10 and 11 are schematic views showing a sixth embodiment of the gas turbine blade according to the present invention. In addition,
FIG. 10 is a plan view in which a part of the wing effective portion is extracted and developed, and FIG. 11 is a cross-sectional view taken along the line BB in FIG. In addition, parts corresponding to the first embodiment are denoted by the same reference numerals.

The gas turbine blade according to the present embodiment has a ventral side 2 of the blade effective portion 20 in contact with the gas turbine driving gas 33.
3, while forming the outlet 26 provided in each of the back side 24 and the wing tip portion 25 in the shape shown in the first embodiment, as shown in FIG. 11, the inlet 3 of the outlet 26
The center line 40 of the passage 39 connecting the nozzle 7 and the outlet 38 is formed so as to be inclined in the direction toward the downstream side of the gas turbine driving gas 33.
A gas turbine drive gas flow direction side diffusion portion 42 having an inclination angle partially toward the upstream side of the gas turbine drive gas 33 at an upstream portion facing the gas turbine drive gas 33.
Is provided to enlarge the passage 39.

As described above, in the present embodiment, the gas turbine driving gas flow reverse direction diffusion portion 42 having a partial inclination angle at the outlet portion 38 of the ejection port 26 is provided and the passage 3 is provided.
9 is enlarged, the diffusivity due to collision between the cooling medium CA flowing along the gas turbine driving gas flow reverse diffusion section 42 and the gas turbine driving gas 33 can be further improved at the position of the outlet section 38. .

In the present embodiment, the gas turbine driving gas flow reverse direction diffusion portion 42 is provided at the outlet 38 of the jet outlet 26 on the side facing the upstream side of the gas turbine driving gas 33. However, the present invention is not limited to this example. For example, as shown in FIGS. 12 and 13, the gas turbine driving gas flow reverse side diffusion portion 42 provided on the side of the outlet portion 38 of the ejection port 26 facing the flow of the gas turbine driving gas 33 has a fifth
The gas turbine driving gas flow direction side diffusion part 41 shown in the embodiment may be combined. This is effective in that the diffusivity of the cooling medium CA is further enhanced.

FIG. 14 is a schematic developed plan view showing a seventh embodiment of the gas turbine blade according to the present invention.

The gas turbine blade according to the present embodiment has a ventral side 2 of the blade effective portion 20 in contact with the gas turbine driving gas 33.
3. Of the outlets 26 provided on the back side 24 and the wing tip portion 25, respectively, the inlet 37 is made common, and the outlets 38, 38 are formed in a plurality, and the common inlet 37
In contrast, a plurality of outlets 38, 38 are connected by passages 39, 39. The outlet 38 of the outlet 26,
Since the shape of 38 is the same as that shown in the first embodiment, the same reference numerals are given and the description is omitted.

As described above, in the present embodiment, a plurality of outlets 3 are connected to the common inlet 37 of the outlets 26.
Since the passages 8 and 38 are connected by a plurality of passages 39 and 39 and the passage area is enlarged, the outer wing of the film ejection flow 30 having a larger momentum of the cooling medium CA and the film ejection flow 30 having a smaller momentum of the cooling medium CA. The film can be allowed to flow out with a margin, and the film film cooling can be further enhanced.

FIG. 15 is a schematic developed plan view showing an eighth embodiment of the gas turbine blade according to the present invention.

The gas turbine blade according to the present embodiment has a ventral side 2 of the blade effective portion 20 in contact with the gas turbine driving gas 33.
3. Of the outlets 26 provided on each of the back side 24 and the wing tip portion 25, the shape of the inlet portion 37 is formed to have a circular cross section, and the shape of the outlet portion 38 is set to be the same as in the first embodiment. The cooling medium C in the central portion where t is smallest
A is formed into a horseshoe shape having a curved surface through which the membrane ejection flow 32 having a large momentum of A flows out and the membrane ejection flow 30 having a small momentum of the cooling medium CA flowing out at an outer portion 31 thereof, and an inlet portion 37 thereof.
And an outlet 38 thereof are connected by a passage 39 which is expanded along the flow direction of the gas turbine driving gas 33.

As described above, in the present embodiment, of the outlet 26, the shape of the inlet portion 37 is formed in a circular cross section, and the shape of the outlet portion 38 is formed in a horseshoe shape. Since the passage 39 connecting to the outlet portion 38 is expanded along the flow direction of the gas turbine driving gas, the film ejection flow 30 in which the momentum of the cooling medium CA is increased.
The film ejection flow 30 having a reduced momentum of the cooling medium CA and the film ejection flow 30 can be allowed to flow out of the blade with a margin, and the film film cooling can be further enhanced.

[0061]

As described above, the gas turbine blade according to the present invention, on the surface of the blade effective portion, forms a film ejection flow with a large momentum of the cooling medium and a film ejection flow with a small momentum of the cooling medium. The combination of the outlets, which are made to flow out, is provided for a long time along the surface of the blade effective portion of the cooling medium and is diffused widely, so that the performance of the film cooling in the form of a film can be further improved.

[Brief description of the drawings]

FIG. 1 is a schematic perspective view showing a first embodiment in which a gas turbine blade is taken as an example as a gas turbine blade according to the present invention.

FIG. 2 is a partially enlarged view showing the blowout port shown in FIG. 1 extracted and expanded.

FIG. 3 is a schematic development plan view showing a second embodiment of the gas turbine blade according to the present invention.

FIG. 4 is a schematic development plan view showing a modification of the second embodiment of the gas turbine blade according to the present invention.

FIG. 5 is a schematic developed plan view showing a third embodiment of the gas turbine blade according to the present invention.

FIG. 6 is a schematic development plan view showing a fourth embodiment of the gas turbine blade according to the present invention.

FIG. 7 is a schematic developed plan view showing a modification of the fourth embodiment of the gas turbine blade according to the present invention.

FIG. 8 is a schematic developed plan view showing a fifth embodiment of the gas turbine blade according to the present invention.

FIG. 9 is a cross-sectional view taken along the line AA of FIG. 8;

FIG. 10 is a schematic developed plan view showing a sixth embodiment of the gas turbine blade according to the present invention.

FIG. 11 is a cross-sectional view taken along the line BB of FIG. 10;

FIG. 12 is a schematic development plan view showing a modification of the sixth embodiment of the gas turbine blade according to the present invention.

FIG. 13 is a cross-sectional view as viewed from the direction of arrows CC in FIG. 12;

FIG. 14 is a schematic developed plan view showing a seventh embodiment of the gas turbine blade according to the present invention.

FIG. 15 is a schematic developed plan view showing an eighth embodiment of the gas turbine blade according to the present invention.

FIG. 16 is a perspective view showing a gas turbine blade as an example of a conventional gas turbine blade.

FIG. 17 is a cross-sectional view taken along the line KK of FIG. 16;

FIG. 18 is a cross-sectional view taken along the line JJ of FIG. 16;

FIG. 19 is a diagram showing an example of the arrangement of jet ports in a conventional gas turbine blade.

FIG. 20 is a cross-sectional view taken along the line LL in FIG. 19;

FIG. 21 is a view showing an example of the arrangement of another ejection port in a conventional gas turbine blade.

FIG. 22 is a view showing an example of the arrangement of another ejection port in a conventional gas turbine blade.

FIG. 23 is a view showing an example of the arrangement of still another ejection port in a conventional gas turbine blade.

FIG. 24 is a schematic development plan view showing still another ejection port in a conventional gas turbine blade.

FIG. 25 is a cross-sectional view taken along the line NN of FIG. 24;

FIG. 26 is a cross-sectional view showing still another ejection port in a conventional gas turbine blade.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Blade effective part 2 Blade implant part 3a, 3b, 3c Cooling passage 4 Front edge 5 Ventral side 6 Back side 7 Blade tip part 8 Spouting port 9 Trailing edge 10 Spouting port 11 Gas turbine drive gas 12 Spouting center line 13 Cooling medium 14 , 15 widening opening 20 wing effective part 21 wing implantation part 22 leading edge 23 ventral side 24 back side 25 wing tip part 26 outlet 27 trailing edge 28 outlet 29 central part 30 membrane discharge flow with reduced momentum 31 outer part 32 momentum Film discharge flow 33 gas turbine drive gas 34 discharge center line 35 first discharge port 36 second discharge port 37 inlet part 38 outlet part 39 passage 40 center line 41 gas turbine drive gas flow direction side diffusion part 42 gas Turbine drive gas flow reverse side diffusion section

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Kazutaka Ikeda 1-1-1, Shibaura, Minato-ku, Tokyo Inside Toshiba Corporation Head Office (72) Inventor Yoshitaka Fukuyama 2-1 Ukishima-cho, Kawasaki-ku, Kawasaki-shi, Kawasaki, Kanagawa Prefecture No. 2 Toshiba Hamakawasaki Plant, Toshiba Corporation (72) Inventor Kotobuki Matsuda 2-1, Ukishima-cho, Kawasaki-ku, Kawasaki City, Kanagawa Prefecture F-term 3G002 CA06 CB01

Claims (11)

[Claims] In a gas turbine blade provided with an outlet for discharging a cooling medium in a film form along the surface of an effective blade portion, a flow of the film is increased by increasing the momentum of the cooling medium at the center of the outlet. A gas turbine blade having a horseshoe shape having a curved surface for letting out a film and ejecting a film jet flow having a reduced momentum of a cooling medium at an outer portion thereof. 2. The gas turbine blade according to claim 1, wherein the horseshoe-shaped outlet has a center of curvature of a curved surface set downstream of the outlet. 3. The gas turbine blade according to claim 1, wherein the horseshoe-shaped outlet has a curvature center position of a curved surface set upstream of the outlet. 4. The horseshoe-shaped outlet has an upward inclination angle in a direction toward a downstream side in which a gas turbine driving gas flows in a center line of the outlet connecting the inlet portion and the outlet portion. The gas turbine blade according to claim 1, wherein: 5. A gas turbine blade having an outlet for discharging a cooling medium in a film form along the surface of an effective blade portion, wherein said outlet is divided into a first outlet and a second outlet. In parallel with each other,
Is formed in a horseshoe shape having a curved surface that allows the membrane ejection flow having a large momentum of the cooling medium to flow out at the center portion thereof and the membrane ejection flow having a small momentum of the cooling medium to flow out at an outer portion thereof. on the other hand,
A gas turbine blade, wherein the second outlet is formed in one of a circular cross section and an elliptical cross section through which a film jet flow having a large momentum of a cooling medium flows out. 6. A gas turbine blade having an outlet for discharging a cooling medium in a film form along the surface of an effective blade portion, wherein said outlet is divided into a first outlet and a second outlet. The first ejection port is disposed on both sides of the second ejection port in the middle of the second ejection port, and the first ejection port flows out of the film ejection flow in which the momentum of the cooling medium is increased at the center thereof. And forming a horseshoe-like shape having a curved surface on the outer portion thereof with a curved surface through which the film jet flow having a reduced momentum of the cooling medium flows out, and the second jet port discharging the film jet flow having a larger momentum of the cooling medium. A gas turbine blade formed in one of a circular cross section and an elliptical cross section to be formed. 7. A gas turbine blade provided with an outlet for discharging a cooling medium in a film form along the surface of an effective blade portion, wherein said outlet is provided with a film jet flow in which the momentum of the cooling medium is increased at a central portion thereof. To form a horseshoe-like shape having a curved surface for flowing out a film jet flow in which the momentum of the cooling medium is reduced at an outer portion thereof, and a center line of a passage connecting an inlet portion and an outlet portion of the jet port is formed. The gas turbine is driven by giving an upward inclination angle in the direction toward the downstream side where the gas turbine driving gas flows, and further giving the center line an inclination angle again in the direction toward the downstream side where the gas turbine driving gas flows at the outlet portion. A gas turbine blade having a gas flow direction side diffusion portion. 8. A gas turbine blade provided with an outlet for discharging a cooling medium in a film form along the surface of an effective blade portion, wherein said outlet is provided with a film jet flow in which the momentum of the cooling medium is increased at a central portion thereof. To form a horseshoe-like shape having a curved surface for flowing out a film jet flow in which the momentum of the cooling medium is reduced at an outer portion thereof, and a center line of a passage connecting an inlet portion and an outlet portion of the jet port is formed. The gas turbine has an upward inclination angle in a direction toward the downstream side where the gas turbine driving gas flows, and further has an inclination angle in the center line in the direction toward the upstream side where the gas turbine driving gas flows again at the outlet portion. A gas turbine blade having a driving gas flow reverse side diffusion portion formed therein. 9. A gas turbine blade provided with an outlet for discharging a cooling medium in a film form along the surface of an effective blade portion, wherein said outlet is provided with a film jet flow in which a momentum of the cooling medium is increased at a central portion thereof. To form a horseshoe shape with a curved surface that allows the film jet flow with a reduced momentum of the cooling medium to flow out at the outer part, and to define the center line of the passage connecting the inlet and outlet of the jet outlet. The gas turbine drive gas has an upward inclination angle in the direction toward the downstream side, and further has its center line directed toward the downstream side where the gas turbine drive gas flows again at the outlet portion and the upstream side where the gas turbine drive gas flows. Gas turbine drive gas flow direction diffusion part and gas turbine drive gas flow reverse direction A gas turbine blade having a diffusion portion. 10. A gas turbine blade provided with an outlet for discharging a cooling medium in a film form along the surface of the blade effective portion, wherein the outlet of the outlet is made common and the outlet is made plural, and And the plurality of outlets are connected by a plurality of passages, and at the outlet of the outlet, a film jet flow in which the momentum of the cooling medium is increased at a central portion thereof flows out, and the cooling medium flows at an outer portion thereof. A gas turbine blade formed in a horseshoe shape having a curved surface through which a membrane jet flow having a reduced momentum flows out. 11. A gas turbine blade having an outlet for discharging a cooling medium in a film form along a surface of an effective blade portion, wherein an inlet of the outlet is formed in a circular cross section.
The outlet of the outlet is formed in a horseshoe shape having a curved surface through which a film jet flow having a reduced momentum of the cooling medium is discharged at a central portion thereof, and a passage connecting the inlet and the outlet is expanded. A gas turbine blade formed in a shape.