JPH1163499A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To raise the cooling capacity and aerodynamic capacity of the cooling structure of a combustor, by providing at least one hand of the combustion area of the inner cylinder of a combustor and the whole area of the inner cylinder of the combustor with a rib, and possessing a ring piece which extends toward an upstream outer cylinder from a downstream outer cylinder dividing the outer cylinder of the combustor. SOLUTION: The barrel of a combustor area 37 is equipped with ribs 39 in the shape of projections arranged at equal intervals in axial direction on its peripheral side. The outer cylinder 23 of the combustor consists of an upstream outer cylinder 23c and a downstream outer cylinder 23d which are made by halving itself in the middle and between whose free ends 23a and 23b an air passage 27 is made. A ring piece 40 is integrated in the free end 23b of the downstream outer cylinder 23d. For this ring piece 40, its upstream side extends to its upstream side so as to cover the whole periphery of the barrel of the combustion area 37, and forms an air supply port 27 between itself and the free end 23a of the upstream outer cylinder 23c, and also its opposite side forms a throttled flow passage between itself and the barrel of the combustion area 37.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor, and more particularly to a gas turbine combustor that effectively cools components of the gas turbine combustor with a limited cooling medium.

[0002]

2. Description of the Related Art In recent gas turbines, the temperature has been remarkably advanced in pursuit of higher output and higher thermal efficiency.
It is increasing to 1500 ° C or more after 0 ° C.

[0003] As described above, the gas turbine combustor is subjected to severe operating conditions amid the high temperature of the gas turbine which rapidly rises at an accelerated rate. There is a response to cooling, which effectively cools its components by using it, and a response to a reduction in the concentration of NOx, which is generated remarkably in association with a high temperature.

[0004] To reduce the concentration of NOx, air is injected into the fuel in advance, referred to as a lean premixed combustion system.
This is addressed by keeping the combustion gas temperature low.

[0005] Further, the cooling of the components of the gas turbine combustor requires a large amount of air to be consumed in the case of so-called film cooling in which air flows in a film form along the wall surface of each component. Convection cooling to increase the heat transfer coefficient by actively disturbing the air,
Air is jet-collimated with each component, and impingement cooling that takes away heat during the collision is combined.

As described above, in recent gas turbine combustors, lean premix combustion systems, convection cooling and impingement cooling, and various types of cooling systems are combined to deal with high temperatures. There is one shown in FIG.

[0007] A gas turbine combustor generally designated by reference numeral 1 is housed in casings 2a and 2b, and has a cylindrical combustor liner 4 (inner cylinder) and a cylindrical combustor in order from upstream to downstream. It has a combustor transition piece 5 (transition piece) and is configured to be connected to a gas turbine stationary blade 7 installed at an inlet of a gas turbine 6. The number of cans of this gas turbine combustor 1 is increased or decreased in accordance with the capacity (output) of the gas turbine 6, and usually 6 to 12 cans are installed.

The gas turbine combustor 1 obtains, from the air compressor 8, air for promoting combustion gas of fuel injected from the combustor nozzle 3 and air for cooling the combustor liner 4 and the combustor transition piece 5. The high-pressure air AR from the air compressor 8 is guided to the combustor liner 4 or the combustor transition piece 5 via the intermediate cylinder 8a, and the film cooling, the convection cooling, and the impingement cooling are skillfully combined, and the combustor liner 4 is cooled. And combustor transition piece 5
Is allowed to cool.

The transition piece 5 is formed as a double cylinder having an outer cylinder 9 and an inner cylinder 10, and an impingement hole 11 is formed along the circumferential direction of the outer cylinder 9.
The high pressure air AR from the air compressor 8 is jet-collimated with the inner cylinder 10 through the impingement hole 11 to cool the inner cylinder 10.

The combustor transition piece 5 has its fixed point on the gas turbine stationary blade 7 side, and can move toward the combustor liner 4 when the combustion gas causes thermal expansion in the axial and radial directions. The end is a free end 12.

On the other hand, in the combustor liner 4, an air passage 14 is formed by a flow sleeve 13 in which the outside is concentrically arranged.

The high-pressure air AR flowing from the free end 15 of the flow sleeve 13 into the high-pressure air AR after the inner cylinder 10 of the combustor transition piece 5 is impinged and cooled.
And a part of the combined air is caused to flow along the inner wall surface of the combustor liner 4 through the cooling holes 16 provided in the combustor liner 4 to perform film cooling, and at the same time to remove the remaining combined air. The outer wall surface of the combustor liner 4 is guided to the combustor nozzle 3 while being cooled by convection, and is supplied to promote generation of fuel combustion gas.

On the other hand, the combustor liner 4 is provided with a stopper 17 between the head sleeve side flow sleeve 13 and a spring seal 18 between the combustor tail tube 5 and the inner cylinder 10 on the downstream side. The fixing point is placed on the stopper 17 so that when the combustion gas causes thermal expansion in the axial direction and the radial direction, the thermal expansion is absorbed by the spring seal 18.

As described above, the conventional gas turbine combustor 1
Then, for the components such as the combustor liner 4 and the combustor transition piece 5,
By skillfully combining film cooling, convection cooling and impingement cooling, the effective use of limited high pressure air AR
While maintaining the strength, it was made to cope with high temperature.

[0015]

The gas turbine has a combustion gas temperature (gas turbine inlet temperature) of 15 degrees.
Nowadays, the temperature is becoming higher than 00 ° C, but even if we try to secure the strength by combining the above-mentioned film cooling, convection cooling, and impingement cooling in the gas turbine combustor, there is a limit in terms of cooling performance and aerodynamic performance naturally, There are several problems listed below.

First, when impingement cooling is enhanced to cope with higher temperatures, impingement holes must be provided throughout the components of the gas turbine combustor. However, when the impingement holes are provided over the entire area of the components of the gas turbine combustor, the high-pressure air is consumed more than before. The high-pressure air is originally supplied to promote the generation of the combustion gas, and if it is consumed in a large amount for impingement cooling, the plant thermal efficiency becomes significantly lower than before and disadvantageous.

Second, it is conceivable to enhance convective cooling. However, since the connecting portion between the combustor transition piece and the gas turbine has a complicated structure, for example, a protruding piece such as a rib for giving a forced turbulence to high-pressure air to increase a heat transfer coefficient is attached. Can not be performed, resulting in damage accident due to insufficient cooling.

Third, it is conceivable to enhance the combined use of impingement cooling and convection cooling. However, the connecting portion between the combustor liner and the combustor transition piece overlaps and overlaps each other, and the thermal expansion due to mutual thermal expansion is absorbed by a spring seal. Is structurally difficult to provide. For this reason, cooling of this part will rely exclusively on film cooling, but if a hole for film cooling is provided, a difference in thermal stress will occur between the hole and the peripheral part deviating from the hole, and with the increase in temperature, The difference in thermal stress becomes more and more difficult to maintain the strength, and the maintenance of the function of the spring seal becomes lower.

Fourth, the flow sleeve and the combustor transition piece are supported by separate casings, and expand separately according to the temperature distribution. In particular, since the flow sleeve has one end supported by the head on the combustor nozzle side and the other end being a free end, there is a deviation from the common axis of the combustor transition piece due to thermal expansion. As a result, the opening area of the cooling passage fluctuates widely. When the opening area of the cooling passage is reduced, the inflow of the merged air is reduced, and convective cooling of the combustor liner is insufficient, and excessive thermal stress is locally generated, thereby causing a burnout accident.

Fifth, the components such as the casing, the combustor transition piece, and the flow sleeve are not so high in mounting accuracy and assembling accuracy. Along with this, variations on the axial center appear, causing a non-uniform combustion gas temperature distribution in the gas turbine, which is not preferable in terms of gas turbine efficiency.

As described above, in the conventional gas turbine combustor, there are structural limitations and the amount of high-pressure air for cooling is limited. He was not able to fully answer with confidence.

The present invention has been made in view of such circumstances, and it is an object of the present invention to provide a gas turbine combustor which can apply a cooling structure having excellent cooling performance and aerodynamic performance.

It is another object of the present invention to provide a gas turbine combustor having a highly reliable support structure when a cooling structure having excellent cooling performance and aerodynamic performance is applied.

[0024]

According to a first aspect of the present invention, there is provided a gas turbine combustor for producing a combustion gas with fuel injected from a firing nozzle. A gas turbine comprising: a combustor inner cylinder that divides into a region part and a transition part that guides the combustion gas to the gas turbine; and a combustor outer cylinder that surrounds the outside of the combustor inner cylinder to form an air passage. In the combustor, a rib is provided on at least one of the combustion region side of the combustor inner cylinder and the entire region of the combustor inner cylinder, and the combustor outer cylinder is divided into an upstream outer cylinder and a downstream outer cylinder. And a ring piece extending from the downstream outer cylindrical portion toward the upstream outer cylindrical portion.

In the gas turbine combustor according to the present invention, the ring piece guides the air between the upstream outer cylindrical portion and the downstream outer cylindrical portion. The air passage opening is formed, and a contraction passage is formed on the combustion region side of the combustor inner cylinder.

In order to achieve the above object, the gas turbine combustor according to the present invention is characterized in that the ring piece is supported by a pin protruding from the upstream outer cylindrical portion. Things.

In order to achieve the above object, the gas turbine combustor according to the present invention is characterized in that the ring piece is supported by a stay extending from the upstream outer cylindrical portion. Things.

According to a fifth aspect of the present invention, there is provided a gas turbine combustor, wherein the ring piece includes a flat portion and a raised portion, and the flat portion is connected to the upstream outer cylindrical portion. And a means for suppressing thermal expansion of the downstream outer cylinder portion in the raised portion.

In the gas turbine combustor according to the present invention, in order to achieve the above object, the means for suppressing the thermal expansion of the downstream outer cylinder portion is provided at the raised portion of the ring piece. The sealing ring is inserted through a holding plate that covers an end of the downstream outer cylindrical portion.

In order to achieve the above object, the gas turbine combustor according to the present invention forms an air passage between the inner cylinder of the combustor and the outer cylinder of the upstream. The air passage is formed as an expanded passage toward the combustor nozzle.

[0031] In the gas turbine combustor according to the present invention, as set forth in claim 8, in order to achieve the above object, the combustor inner cylinder is a cylinder in which a combustion region portion and a transition portion are continuously and integrally formed. It is characterized by being a torso-shaped body.

According to a ninth aspect of the present invention, a gas turbine combustor according to the present invention has a head side of a combustor inner cylinder having a transition inner cylinder duct connected to a combustor liner. A main fuel portion having a pilot fuel nozzle and a premixing fuel nozzle and a main fuel nozzle and a premixing duct outside the combustor inner cylinder, while the combustor inner cylinder and the main In a gas turbine combustor having a combustor outer cylinder surrounding a fuel unit,
While providing a rib on the combustor liner, the combustor outer cylinder is divided into an upstream outer cylinder portion and a downstream outer cylinder portion, and a ring piece extending from the downstream outer cylinder portion toward the upstream outer cylinder portion is provided. A seal portion is provided at a connection portion between the combustor liner and the transition inner cylinder duct.

[0033] The gas turbine combustor according to the present invention achieves the above-mentioned object.
The premixing duct is one in which a duct spring is interposed and covered with a jacket, and the outlet of the premixing duct is inserted through a collar provided in a combustion liner.

[0034] A gas turbine combustor according to the present invention achieves the above object by providing,
The duct spring is a leaf spring.

A gas turbine combustor according to the present invention achieves the above object by providing
A seal portion provided at a connection portion between the combustor liner and the transition inner cylinder duct is a leaf spring. One end of the leaf spring abuts on a receiving portion provided on the combustion liner, and the other end of the combustor has the other end. This is fixed to the end of the liner and applies a pressing force to the transition inner cylinder duct.

The gas turbine combustor according to the present invention achieves the above object by providing
The leaf spring is characterized by forming a slit.

[0037] A gas turbine combustor according to the present invention achieves the above object by providing,
The combustor liner covered with the seal portion has a groove formed at an end and a rib provided between the groove and the receiving portion.

[0038]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a gas turbine combustor according to the present invention will be described below with reference to the accompanying drawings and part numbers given in the drawings.

FIG. 1 is a partially cutaway schematic assembly sectional view showing a first embodiment of a gas turbine combustor according to the present invention.

The gas turbine combustor 20 according to this embodiment
Includes a combustor nozzle 22, a combustor outer cylinder 23, and a combustor inner cylinder 24 in this order along the flow of the combustion gas from the upstream side to the downstream side. The outlet end of the cylinder 24 is connected to a gas turbine stationary blade 26 installed at the inlet of the gas turbine 25. The gas turbine combustor 20 has a plurality of cans arranged in a ring with respect to the gas turbine 25.

The outer cylinder 23 of the combustor is divided into two parts on the way, and the free ends 23a and 23b
Are provided with an upstream outer tube portion 23c and a downstream outer tube portion 23d. The upstream outer cylinder portion 23c concentrically surrounds the outside of the combustor inner cylinder 24 to form an air passage 27a, and forms the head side of the expansion passage 28, while forming a support portion 29 in the middle thereof. And is fixed to the casing 21a.

The support portion 29 has a block 29a fixed to the upstream outer tube portion 23c and a block 29b fixed to the combustor inner tube 24, and a groove formed in the block 29a fixed to the upstream outer tube portion 23c. A block 29 fixed to the combustor inner cylinder 24 can be inserted into the combustor inner cylinder 24 and slidably moved. In addition, this support part 29 is installed in three places along the circumferential direction of the upstream outer cylinder part 23c and the combustor inner cylinder 24, for example. Further, the joint between the combustor inner cylinder 24 and the combustor nozzle 22 has a structure in which metals are joined to each other or a leaf spring is interposed. This part
Since the temperature is relatively low, even if thermal expansion occurs in the axial direction, the slide can be performed, so that excessive stress is not generated. The joint between the combustor inner cylinder 24 and the combustor nozzle 22 may have a joint structure formed by fitting a gap.

The downstream outer cylinder portion 23d surrounds the outside of the combustor inner cylinder 24 to form an air passage 30 and has an impingement hole 31 provided along the circumferential direction thereof.
The high-pressure air AR supplied through the intermediate cylinder 33 is guided to the impingement hole 31, where it is jet-collimated with the combustor inner cylinder 24 to be cooled.

The downstream outer cylinder portion 23d is fixed to the inside of the casing 21b via a mounting member 34 on the inside thereof, and is supported downstream by a support member 35 extending from the gas turbine 25. Further, the outlet ends of the downstream outer cylinder portion 23d and the combustor inner cylinder 24 are both supported by support pieces 36 protruding from the gas turbine 25.

On the other hand, the combustor inner cylinder 24 has a combustion region 37 for generating combustion gas with fuel injected from the combustion nozzle 22 on the upstream side thereof, and a combustion gas generated in the combustion region 37 for the gas turbine 25. It is divided into a throttle-shaped transition portion 38 for guiding to the gas turbine stationary blade 26, and has a cylindrical body structure in which the combustion region portion 37 and the transition portion 38 are continuously and integrally formed.

The body of the combustion area portion 37 is provided with protruding ribs 39 arranged at equal intervals along the axial direction on the outer peripheral side thereof. The rib 39 may be integrally cut with the body of the combustion region 37, or may be separately manufactured from the body of the combustion region 37 and joined by welding or the like. Also, this rib 39
When integrally cutting from the body of the combustion area portion 37, the cutting may be performed in an inclined manner with respect to the radial direction of the body using a cutting machine equipped with numerical control. Although the combustion region portion 37 and the transition portion 38 are formed as a body integrally continuous along the axial direction, the body of the combustion region portion 37 is a circular cylindrical shape, and the body of the throttle-shaped transition portion 38 is formed. Are formed in a fan-shaped quadrilateral and have different shapes from each other. Therefore, if fusion joining or diffusion joining is applied to the connecting portion between the body of the combustion region portion 37 and the body of the transition portion 38, the cost can be reduced. , Can be connected smoothly.

On the other hand, the free end 23b of the downstream outer cylinder portion 23d disposed outside the body of the transition portion 38 is provided with a ring valve 40.
Is incorporated. As shown in FIG. 2, the ring piece 40 extends upstream so as to cover the entire periphery of the body of the combustion region portion 37, and connects the air supply port 27 with the free end 23a of the upstream outer cylindrical portion 23c. In addition, a contraction passage 41 is formed between the body and the body of the combustion region 37 on the opposite side.

Next, the operation will be described.

The outer surface of the combustor inner cylinder 24, which forms the combustion region portion 37 and the transition portion 38 as a continuously integrated body, is cooled by the high-pressure air AR supplied from the air compressor 32.

First, the high-pressure air AR is supplied to the impingement hole 31 provided in the circumferential direction of the downstream outer cylinder portion 23 d through the intermediate cylinder 33 of the air compressor 32, where the impingement hole 31 jets against the body of the transition portion 38. At the time of the collision, heat is taken and the body of the transition section 38 is cooled. The high-pressure air AR that has cooled the body of the transition section 38 flows through the contraction passage 41 formed by the ring piece 40 and the body of the combustion area section 37, as shown in FIG. In this case, the high-pressure air AR that has jet-collimated with the body of the transition portion 38 has a low axial flow velocity, but is accelerated when passing through the contraction passage 41, and further increases in the combustion region portion 37.
The flow is disturbed by the ribs 39 provided on the body, and the heat transfer coefficient is improved, so that the body of the transition portion 38 and the body of the combustion region 37 can be cooled well.

The high-pressure air AR that has exited the contraction passage 41 is disturbed by the ribs 39 and has a large pressure loss. However, the high-pressure air AR that has exited the contraction passage 41 is supplied to the high-pressure air guided from the air passage opening 27 formed between the free end 23a of the upstream outer cylinder 23c and the free end 23b of the downstream outer cylinder 23d. Because it is attracted by the ejector effect of AR,
The air can be satisfactorily merged and flown into the air passage 27a of the body of the combustion area portion 37.

As shown in FIG. 1, when the high-pressure air AR joined at the outlet side of the contraction passage 41 flows through the air passage 27a, the flow is disturbed by the ribs 39 to increase the heat transfer coefficient, thereby increasing the heat transfer coefficient. After the body is cooled by convection, the pressure is recovered in the expansion passage 28 and supplied to promote generation of combustion gas of the fuel injected from the fuel nozzle 22.

On the other hand, the upstream outer cylindrical portion 23c is configured such that the blocks 29a and 29b of the support portion 29 provided on the head side thereof are slidable, and its end is a free end 23a.
Since the thermal expansion is released to the body side of the transition portion 38, excessive thermal stress is not generated in the body of the combustion region portion 37. Further, the downstream outer cylindrical portion 23d is also configured such that one end is a free end 23b and the other end is supported by a support member 35 and a support piece 36 so that thermal expansion is released to the body side of the combustion region portion 37. It can sufficiently cope with elongation.

As described above, in the present embodiment, the combustor inner cylinder 24 divided into the combustion region portion 37 and the transition portion 38 is formed as a continuously integrated body, and the combustor outer cylinder surrounding the combustor inner tube 24 is formed. 23 is a combination of the upstream outer cylindrical portion 23c and the downstream outer cylindrical portion 23d.
The impingement hole 31 is divided and provided in the downstream outer cylindrical portion 23d.
Transition section 3 with high-pressure air AR from air compressor 32 via
8 is cooled by impingement, and the high-pressure air AR after impingement cooling is reduced by the contraction passage 4 formed by the ring pieces 40.
1, the convection cooling of the body of the combustion region 37 is performed.
Further, the high-pressure air AR supplied from an air passage opening 27 formed between the upstream outer cylindrical portion 23c and the downstream outer cylindrical portion 23d.
The high pressure air AR after the impingement cooling is attracted and merged, and the combined air disturbs the ribs 39 provided on the body of the combustion region 37 to convectively cool the body of the combustion region 37. Even with high-pressure air, good cooling can be performed without generating excessive thermal stress in the inner cylinder of the combustor, and it is possible to sufficiently cope with high temperature.

FIG. 3 is a partially schematic enlarged view showing a first example of the combustor outer cylinder in the first embodiment of the gas turbine combustor according to the present invention. The same reference numerals are given to the same or corresponding parts as the components of the first embodiment.

In the present embodiment, the combustor outer cylinder 23 is divided into an upstream outer cylinder 23c and a downstream outer cylinder 23d, and the free end 23b of the downstream outer cylinder 23d is connected to the body of the combustion area 37. A ring piece 40 forming a contraction passage 41 therebetween is incorporated, and a pin 43 fixed to a free end 23a of an upstream outer cylindrical portion 23c is inserted through a pin hole 44 provided in a protruding piece 42 of the ring piece 40. It is.

The ring piece 40 is formed along the circumferential direction of the body of the combustion area portion 37. The diameter of the pin hole 44 of the protruding piece 42 is slightly larger than the diameter of the pin 43, so that the position error of the pin hole 44 and the upstream The thermal expansion of the outer cylindrical portion 23c can be sucked.

In this embodiment, the free end 2 of the downstream outer cylindrical portion 23d is used.
Since the pin 43 fixed to the free end 23a of the upstream outer cylindrical portion 23c is inserted into the projecting piece 42 of the ring piece 40, the operation of the upstream outer cylindrical portion 23c and the downstream outer cylindrical portion 23d is performed. Can prevent misalignment during
Mutual thermal elongation can also be absorbed.

FIG. 4 is a partially cutaway schematic sectional view showing a second embodiment of the gas turbine combustor according to the present invention. Note that the same reference numerals are given to the components of the first embodiment or corresponding parts.

In this embodiment, the combustion region 37 and the transition 3
The rib 39 is provided over the entire outer surface of the combustor inner cylinder 24, which is formed as a continuously integrated body, and the combustor outer cylinder 23 is divided into an upstream outer cylinder 23c and a downstream outer cylinder 23. 23d, the air passage opening 27 is formed, and the ring piece 40 is incorporated into the free end 23b of the downstream outer cylinder part 23d, while the stay 45 is provided between the ring piece 40 and the upstream outer cylinder part 23c. Things.

In the present embodiment, unlike the first embodiment, the rib 3 is extended to the body of the transition portion 38 of the combustor inner cylinder 24.
9 and the impingement cooling by the impingement holes 31 and the convection cooling by the ribs 39 are combined.
The high pressure air AR supplied from the air compressor 32 can be reduced to cool the body of the transition section 38 satisfactorily, and the reduced high pressure air AR can be directed to the generation of combustion gas to improve plant thermal efficiency. Can be. In the present embodiment, when cooling the body of the transition portion 38 of the combustor inner cylinder 24, the high-pressure air AR consumed for cooling is reduced by using both impingement cooling and convection cooling.
Unlike the first embodiment, the pitch of the impingement holes 31 is increased and the diameter thereof is reduced.

In this embodiment, as shown in FIG.
While the ring piece 40 is incorporated into the free end 23b of the downstream outer cylindrical part 23d of the upstream outer cylindrical part 23c and the downstream outer cylindrical part 23d, the stay 45 is inserted between the ring piece 40 and the upstream outer cylindrical part 23c. Since it is provided, the misalignment between the upstream outer cylinder portion 23c and the downstream outer cylinder portion 23d can be prevented, and the high-pressure air A supplied from the air passage opening 27 along with the misalignment prevention can be prevented.
R effectively draws the high-pressure air AR passing through the contraction passage 44, and changes the shape of the body of the combustion region 37 and the transition portion 38.
And the body can be uniformly cooled.

FIG. 6 is a partially schematic enlarged view showing a first example of a combustor outer cylinder in a second embodiment of the gas turbine combustor according to the present invention. The same reference numerals are given to the same or corresponding parts as the components of the second embodiment.

In this embodiment, the upstream outer cylindrical portion 23c divided into two
The airtightness of the ring piece 40 incorporated in the free end 23b of the downstream outer cylindrical portion 23d of the downstream outer cylindrical portion 23d, and the absorption of movement due to thermal elongation are achieved.

The ring piece 40 has a flat portion 46 and a raised portion 47.
And formed. The flat portion 46 is provided at the upstream outer cylindrical portion 23c.
Is provided. In addition, the raised portion 47
Are inserted through a presser plate 49 surrounding the free end 23b of the downstream outer cylindrical portion 23d via a seal ring 48. Further, the free end 23b supports the end of the downstream outer cylindrical portion 23d and is sealed with the outer cover 50.

As described above, in the present embodiment, the seal ring 48 provided on the raised portion 47 of the ring piece 40 is
3d is inserted through the holding plate 49 of the free end 23b to utilize frictional contact, and the free end 23b and the downstream outer cylindrical portion 23d are used.
Of the air passage 3
The sealing of the high-pressure air AR flowing from 0 to the contraction passage 44 can be ensured, and thermal expansion can be absorbed by utilizing frictional contact. Combination with cooling can be reliably performed.

FIG. 7 is a partially cutaway schematic assembly sectional view showing a third embodiment of the gas turbine combustor according to the present invention. Note that the same reference numerals are given to the components of the first embodiment or corresponding parts.

The gas turbine combustor 20 according to the present embodiment
Is a combustor inner cylinder which is divided into a combustion region portion 37 for generating combustion gas and a transition portion 38 for guiding the generated combustion gas to the gas turbine stationary blades 26 of the gas turbine 25 to form a continuously integrated body. 24 is formed into two parts, a combustor liner 51 that generates combustion gas and a throttle-shaped transition inner cylinder duct 52 that guides the generated combustion gas to the gas turbine stationary blades 26 of the gas turbine 25. A seal portion 53 is provided at a connection portion between the internal combustion engine and the transition inner cylinder duct 52, and a main fuel portion 54 is provided outside the combustor liner 51.

It is known that as the temperature of the gas turbine 25 increases, the NOx concentration of the combustion gas generated from the gas turbine combustor 20 increases in proportion to the temperature. For this reason, in the present embodiment, a pilot fuel nozzle 55 and a premixing fuel nozzle 56 are provided at the head of the combustor liner 51, and the combustor liner 51 is A flame holding (fire type) is secured by the pilot fuel injected into the fuel injector 51, and based on the flame holding, the fuel injected from the premixing fuel nozzle 56 to the combustor liner 51 is expanded from the air compressor 32 to the air passage 27a. Road 2
8. Pilot fuel injected from the pilot fuel nozzle 55 to the combustor liner 51 when the gas turbine 25 has an intermediate load by generating combustion gas with premixed fuel to which the high-pressure air AR guided through the air port 57 is added. And high-pressure air AR is added to the main fuel injected from the main fuel section 54 to premix the fuel, and the premixed fuel MF generates a combustion gas for driving the gas turbine, and the N contained in the combustion gas is reduced.
It is a low concentration of Ox.

The main fuel section 54 includes a main fuel nozzle 61 connected from a main fuel port 58 via a main fuel head 60 of a head plate 59, and a casing 21a.
And a premixing duct 62 which is housed in the inside and is covered by a jacket 63 along the axial direction of the upstream outer cylindrical portion 23c.

As shown in FIG. 8, the premix duct 62
8 along the circumferential direction of the cylindrical combustor liner 51 as an example.
Are provided. In addition, the premixing duct 62 is
For example, a duct spring 64 such as a leaf spring is interposed therebetween, and is pressed and supported toward the center of the combustor liner 51 by the elastic force of the duct spring 64.

The outer cover 63 is connected to one of the premixing ducts 6.
2 and the adjacent premixing duct 62 are formed in the concave portion 65, the opening area of the air passage 27a is reduced, the high-pressure air AR passing therethrough is increased, the heat transfer coefficient is increased, and the combustor liner is increased. 51 is improved in convection cooling.

The premix duct 62 has a premix duct outlet 66 extending in the radial direction of the combustor liner 51.
And a collar 67 for supporting the premix duct outlet 66. As shown in FIG. 9, the collar 67 supporting the premix duct outlet 66 is formed integrally with the combustor liner 51, and its diameter is set to be relatively larger than that of the premix duct outlet 66 to provide a gap 68. The displacement of the premix duct outlet 66 which expands due to the heat of the premix fuel MF is absorbed.

On the other hand, as shown in FIG. 7, the combustor outer cylinder 23 surrounding the combustor liner 51 provided with the rib 39 along the axial direction and the transition inner cylinder duct 52 is divided into two parts as shown in FIG. An upstream outer tube portion 23c and a downstream outer tube portion 23d forming an air passage opening 27 at the divided free ends 23a and 23b are provided. The upstream outer tube portion 23c surrounds the outside of the combustor liner 51 to form an air passage 27a, and the downstream outer tube portion 23d forms the air passage 30 between the upstream outer tube portion 23d and the transition inner tube duct 52.

The downstream outer cylindrical portion 23d has its free end 2
A ring piece 40 extending from the upper end 3b toward the upstream side and overlapping the free end 23a of the upstream outer cylinder portion 23c is incorporated, and the combustor liner 51 and the transition inner cylinder duct 52
Is provided with a seal portion 53 at the connection portion with.

As shown in FIG. 10, the connecting portion between the combustor liner 51 and the transition inner cylinder duct 52 has the transition inner cylinder duct 52 overlapped on the combustor liner 51, and A seal portion such as a leaf spring, for example, having one end fixed to the end portion 69 of the combustor liner 51 and the other end abutting on a receiving portion 70 provided on the combustor liner 51 between the inner cylinder duct 52 and the transition inner cylinder duct 52. 53 are provided. This seal part 5
Numeral 3 is provided along the circumferential direction of the combustion liner 51 to press the transition inner cylinder duct 52 and form a slit 71 at an appropriate position in the circumferential direction. The combustor liner 51 is provided with ribs 39 at equal intervals in a direction intersecting the axial direction, and an end 6 for supporting and fixing the seal portion 53.
9, a concave groove 72 extending in the axial direction is formed.

At the connection between the combustor liner 51 and the transition inner cylinder duct 52 thus constructed, the air passage 3
The high-pressure air AR supplied from the fuel cell liner 0 through the slit 71 of the seal portion 53 has a rib 3 of the combustor liner 51.
9, where the flow is divided into the receiving portion 70 side and the groove 72 side. During this time, the flow is disturbed by the rib 39, the convection cooling is performed by increasing the heat transfer coefficient, and the combustor liner 51 is cooled. Further, the high-pressure air AR flows into the groove 72 and causes the end 69 of the combustor liner 51 to convectively cool. On the other hand, receiving part 7
The high-pressure air AR flowing to zero flows through the gap 73 to the upstream side of the combustor liner 51, where it joins with the high-pressure air AR from the air passage 30, and disturbs the combined air by the rib 39, The combustor liner 51 is subjected to convection cooling.

As described above, in this embodiment, the connection portion between the combustion liner 51 and the transition inner cylinder duct 52 is uniformly cooled over the entire circumferential area by the limited high-pressure air AR. It is possible to sufficiently cope with the high temperature of the gas turbine 25 without generating excessive thermal stress in the portion.

[0079]

As described above, in the gas turbine combustor according to the present invention, the inside of the combustor which divides the combustion area for generating the combustion gas and the transition section for supplying the generated combustion gas to the gas turbine is provided. A rib is provided on at least one of the entire region of the cylinder and the body of the combustion region,
Impingement holes are formed in the downstream outer cylinder surrounding the outside of the body of the transition section, and cooling is performed by combining convection cooling and impingement cooling over the entire area of the combustor inner cylinder, so combustion with limited high-pressure air The inner cylinder can be cooled uniformly, and the temperature of the gas turbine can be sufficiently increased.

Further, in the gas turbine combustor according to the present invention, the outside of a combustor inner cylinder which is divided into a combustion region for generating combustion gas and a transition portion for supplying the generated combustion gas to the gas turbine is formed. The combustor outer cylinder is divided into the outer cylinder portion and the downstream outer cylinder portion, and a ring piece is incorporated at an end of the divided downstream outer cylinder portion to form a contraction passage, and the high pressure flowing through the contraction passage is formed. The connection between the fuselage in the combustion zone and the fuselage in the transition zone was convectively cooled with air, so that the strength was sufficiently high against the high temperature of the gas turbine without generating excessive thermal stress at the connection. Can be maintained.

Further, the gas turbine combustor according to the present invention comprises:
The combustor outer cylinder is divided into an upstream outer cylinder and a downstream outer cylinder,
A ring piece is incorporated into the end of the downstream outer cylindrical portion divided into two to form a contraction passage, and the high-pressure air passing through the contraction passage is used to reduce the ejector effect of the high-pressure air supplied from the air passage on the opposite side of the ring piece. Since it is utilized and induced, the pressure loss of the high-pressure air can be reduced, and the upstream side of the inner cylinder of the combustor can be convectively cooled.

[Brief description of the drawings]

FIG. 1 is a partially cutaway schematic assembly sectional view showing a first embodiment of a gas turbine combustor according to the present invention.

FIG. 2 is a partially schematic enlarged view of a combustor outer cylinder in the first embodiment of the gas turbine combustor according to the present invention.

FIG. 3 is a partially schematic enlarged view showing a first example of a combustor outer cylinder in the first embodiment of the gas turbine combustor according to the present invention.

FIG. 4 is a partially cut-away schematic assembly sectional view showing a second embodiment of the gas turbine combustor according to the present invention.

FIG. 5 is a partial schematic enlarged view of a combustor outer cylinder in a second embodiment of the gas turbine combustor according to the present invention.

FIG. 6 is a partial schematic enlarged view showing a first example of a combustor outer cylinder in a second embodiment of the gas turbine combustor according to the present invention.

FIG. 7 is a partially cutaway schematic assembly sectional view showing a third embodiment of the gas turbine combustor according to the present invention.

8 is a sectional view taken along the line AA of FIG. 7;

FIG. 9 is a partially enlarged sectional view of FIG. 8;

FIG. 10 is a schematic perspective view showing a connection portion between a combustor liner and a transition inner cylinder duct in a third embodiment of the gas turbine combustor according to the present invention.

FIG. 11 is a partially cut-away schematic sectional view showing a conventional gas turbine combustor.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Gas turbine combustor 2a Casing 2b Casing 3 Combustor nozzle 4 Combustor liner 5 Combustor transition piece 6 Gas turbine 7 Gas turbine stationary blade 8 Air compressor 8a Intermediate cylinder 9 Outer cylinder 10 Inner cylinder 11 Impinge hole 12 Free end 13 Flow sleeve 14 Air passage 15 Free end 16 Cooling hole 17 Stopper 18 Spring seal 20 Gas turbine combustor 21a Casing 21b Casing 22 Combustor nozzle 23 Combustor outer cylinder 23a Free end 23b Free end 23c Upstream outer cylinder 23d Downstream outer cylinder 24 Combustor inner cylinder 25 Gas turbine 26 Gas turbine stationary blade 27 Air passage opening 27a Air passage 28 Expanding passage 29 Support portion 29a Block 29b Block 29c Groove 30 Air passage 31 Impingement hole 32 Air compressor 33 Intermediate cylinder 34 Mounting metal 35 support member 36 support piece 37 combustion area part 38 transition part 39 rib 40 ring piece 41 contraction passage 42 protruding piece 43 pin 44 pin hole 45 stay 46 flat part 47 raised part 48 seal ring 49 holding plate 50 jacket 51 combustor Liner 52 Transition inner cylinder duct 53 Seal part 54 Main fuel part 55 Pilot fuel nozzle 56 Premix fuel nozzle 57 Air port 58 Main fuel port 59 Head plate 60 Main fuel header 61 Main fuel nozzle 62 Premix duct 63 Coating 64 Duct Spring 65 Concave part 66 Premix duct outlet 67 Collar 68 Gap 69 End 70 Receiver 71 Slit 72 Groove 73 Gap

Claims (14)

[Claims] 1. A combustor inner cylinder that divides a combustion region into a combustion region that generates combustion gas with fuel injected from a combustor nozzle and a transition portion that guides the combustion gas to a gas turbine. A gas turbine combustor having a combustor outer cylinder surrounding the air path and providing a rib on at least one of the combustion region side of the combustor inner cylinder and the entire area of the combustor inner cylinder, A gas turbine combustor characterized in that the combustor outer tube is divided into an upstream outer tube portion and a downstream outer tube portion, and a ring piece extending from the downstream outer tube portion toward the upstream outer tube portion. 2. The ring piece has an air passage opening for guiding air between the upstream outer cylinder portion and the downstream outer cylinder portion, and has a contraction passage formed on the combustion region side of the combustor inner cylinder. The gas turbine combustor according to claim 1, wherein: 3. The gas turbine combustor according to claim 1, wherein the ring piece is supported by a pin protruding from the upstream outer cylindrical portion. 4. The gas turbine combustor according to claim 1, wherein the ring piece is supported by a stay extending from the upstream outer cylindrical portion. 5. The ring piece includes a flat portion and a raised portion,
The gas turbine combustor according to claim 1, wherein the flat portion is supported by a stay extending from the upstream outer cylinder portion, and the raised portion includes means for suppressing thermal expansion of the downstream outer cylinder portion. 6. A means for suppressing thermal expansion of the downstream outer cylinder portion,
6. The gas turbine combustor according to claim 5, wherein a seal ring provided on the protruding portion of the ring piece is inserted into a pressing plate that covers an end of the downstream outer cylindrical portion. 7. An air passage is formed between a combustor inner cylinder and an upstream outer cylinder portion, and the air passage is formed as a widening passage toward a combustor nozzle side. A gas turbine combustor as described. 8. The gas turbine combustor according to claim 1, wherein the inner cylinder of the combustor is a cylindrical body that continuously and integrally forms a combustion region and a transition portion. 9. A combustor liner having a transition inner cylinder duct connected to a transition inner cylinder duct, a pilot fuel nozzle and a premixing fuel nozzle provided on a head side of the combustor inner cylinder, and a main fuel nozzle provided outside the combustor inner cylinder. In a gas turbine combustor provided with a main fuel portion provided with a fuel nozzle and a premixing duct, and a combustor outer tube surrounding the combustor inner tube and the main fuel portion, a rib is provided on the combustor liner. The combustor outer tube is divided into an upstream outer tube portion and a downstream outer tube portion, and a ring piece extending from the downstream outer tube portion toward the upstream outer tube portion is provided. A gas turbine combustor comprising a seal portion at a connection portion with an inner cylinder duct. 10. The premix duct is covered by a jacket with a duct spring interposed, and an outlet of the premix duct is inserted into a collar provided in a combustion liner. A gas turbine combustor as described. 11. The gas turbine combustor according to claim 10, wherein the duct spring is a leaf spring. 12. A seal provided at a connection portion between the combustor liner and the transition inner cylinder duct is a leaf spring. One end of the leaf spring abuts on a receiving portion provided on the combustion liner, The gas turbine combustor according to claim 9, wherein an end is fixed to an end of the combustor liner, and a pressing force is applied to the transition inner cylinder duct. 13. The gas turbine combustor according to claim 12, wherein the leaf spring forms a slit. 14. The combustor liner covered by a seal portion, wherein a groove is formed at an end and a rib is provided between the groove and the receiving portion. Gas turbine combustor.