Gas turbine combustor having contraction member on inner wall surface

In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film air (cooling air) are provided with respect to a combustor inner cylinder (42), and contraction members (71, 72, and 73) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (42). The contraction members (71, 72, and 73) are provided in a predetermined area in the circumferential direction excluding penetrating portions (74, 75, and 76), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.

FIELD

The present invention relates to a gas turbine combustor that supplies fuel to compressed gas and mixes the fuel with the compressed gas, and burns the mixed gas to obtain combustion gas, and to a gas turbine that drives a turbine by combustion gas from the gas turbine combustor to obtain rotational power.

BACKGROUND

For example, a gas turbine includes a compressor, a combustor, and a turbine. Air is taken in from an air inlet and compressed by a compressor, and then the air becomes high-temperature and high-pressure compressed air. In the combustor, fuel is supplied to the compressed air to burn the fuel, so that high-temperature and high-pressure combustion gas is obtained. The turbine is then driven by the combustion gas to drive a generator connected to the turbine.

In such a gas turbine combustor, in order to prevent flashback and burnout of wall surfaces, outside air is taken in from an external wall of a combustion chamber positioned near an apical end of a premixing nozzle, and the taken outside air flows along an inner wall surface of the combustion chamber as film air. However, the film air cools the combustion gas quickly in a part-load operation area of the gas turbine in which the temperature of the combustion gas in the combustor is low. Therefore, the timing of burning fuel gas (for example, methane) to cause a chemical reaction from carbon monoxide (CO) to carbon dioxide (CO2) is delayed, and carbon monoxide and unburned hydrocarbon (UHC) may be generated in a large quantity.

As a technique for solving such a problem, for example, there is a technique described in Patent Literature 1 mentioned below. In a gas turbine combustor described in Patent Literature 1, a ring-shaped contraction member in a frustoconical shape is mounted concentrically on an inner cylinder wall at the back of the combustor. Therefore, film air flows toward a central part by the contraction member and is mixed with high-temperature combustion gas to promote a combustion reaction, thereby enabling to suppress generation of carbon monoxide and unburned hydrocarbon.

CITATION LIST

Patent Literature

SUMMARY

Technical Problem

In the conventional gas turbine combustor described above, in a part-load operation area of the gas turbine in which the temperature of combustion gas in the combustor is low, film air is mixed with high-temperature combustion gas by the contraction member to promote a combustion reaction, thereby enabling to suppress generation of carbon monoxide and unburned hydrocarbon. However, in a rated-load operation area of the gas turbine in which the temperature of combustion gas is high, swirl generated by the contraction member may excessively promote a combustion reaction, and thus unstable combustion may occur due to the instability of the swirl itself.

The present invention has been achieved to solve the above problems, and an object of the present invention is to provide a gas turbine combustor and a gas turbine that can suppress generation of carbon monoxide and suppress the occurrence of unstable combustion.

Solution to Problem

According to an aspect of the present invention, a gas turbine combustor includes: a combustion chamber in which high-pressure air and fuel are burned to generate combustion gas; a combustion high-pressure-air supplying unit that supplies combustion high-pressure air to the combustion chamber; a fuel supplying unit that supplies fuel to high-temperature air in the combustion chamber; a cooling-air supplying unit that supplies cooling air to the combustion chamber along an inner wall surface thereof; and a contraction member arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the combustion chamber. The contraction member is provided in a predetermined area in a circumferential direction excluding penetrating portions, which do not disturb flow of cooling air.

In the gas turbine combustor, the contraction member is divided in plural through the penetrating portions and arranged in a circumferential direction.

In the gas turbine combustor, the contraction members are provided at asymmetric positions with respect to a circumferential direction on the inner wall surface of the combustion chamber.

In the gas turbine combustor, the contraction member has a corner portion protruding toward a central part of the combustion chamber.

In the gas turbine combustor, the contraction member is provided in plural in a flow direction of combustion gas.

According to another aspect of the present invention, a gas turbine supplies fuel to compressed air compressed by a compressor to burn fuel in a combustor, and supplies generated combustion gas to a turbine to obtain rotational power. The combustor includes a combustion chamber, a combustion high-pressure-air supplying unit that supplies combustion high-pressure air to the combustion chamber, a fuel supplying unit that supplies fuel to high-temperature air in the combustion chamber, a cooling-air supplying unit that supplies cooling air to the combustion chamber along an inner wall surface thereof, and a contraction member arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the combustion chamber. The contraction member is provided in a predetermined area in a circumferential direction excluding penetrating portions, which do not disturb flow of cooling air.

Advantageous Effects of Invention

According to the gas turbine combustor of the present invention, there are provided a combustion high-pressure-air supplying unit that supplies combustion high-pressure air to a combustion chamber, a fuel supplying unit that supplies fuel to high-temperature air in the combustion chamber, a cooling-air supplying unit that supplies cooling air to the combustion chamber along an inner wall surface, and a contraction member arranged along a circumferential direction on the inner wall surface in a downstream of a flow direction of combustion gas in the combustion chamber. The contraction member is provided in a predetermined area in the circumferential direction excluding penetrating portions, which do not disturb the flow of cooling air. Accordingly, in an area where the contraction member is provided in the combustion chamber, the flow of cooling air is disturbed by the contraction member so that cooling air flows toward a central part. Furthermore, cooling air that flows in from a downstream of the contraction member is also disturbed by the disturbance caused by the contraction member. Therefore, cooling air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby enabling to suppress generation of carbon monoxide and unburned hydrocarbon. On the other hand, in an area where the penetrating portions are provided, the flow of cooling air is not disturbed and cooling air flows along the inner wall surface. Accordingly, abnormal combustion of unburned premixed gas can be prevented, and the instability of swirl can be avoided by the presence of the penetrating portions. As a result, generation of unstable combustion can be suppressed.

According to the gas turbine combustor of the present invention, because the contraction member is divided in plural through penetrating portions and arranged in a circumferential direction, combustion is not excessively promoted in the penetrating portions, thereby enabling to suppress generation of unstable combustion.

According to the gas turbine combustor of the present invention, because the contraction members are provided at asymmetric positions with respect to the circumferential direction on the inner wall surface of the combustion chamber, a flame pattern becomes unbalanced with respect to the circumferential direction. Therefore, the temperature distribution in the circumferential direction in the combustion chamber changes, and thus an excitation force that generates unstable vibration in an axial direction can be reduced.

According to the gas turbine combustor of the present invention, because corner portions protruding toward a central part of the combustion chamber are provided in the contraction member, cooling air generates swirl at the corner portions of the contraction member, thereby enabling to promote mixing of combustion gas and cooling air.

According to the gas turbine combustor of the present invention, because a plurality of contraction members are arranged in the flow direction of combustion gas, heat generation by the contraction members can be dispersed, and generation of carbon monoxide and unburned hydrocarbon can be suppressed.

Furthermore, according to the gas turbine of the present invention, the gas turbine includes a compressor, a combustor, and a turbine, and as the combustor, a combustion high-pressure-air supplying unit that supplies combustion high-pressure air to a combustion chamber, a fuel supplying unit that supplies fuel to high-temperature air in the combustion chamber, a cooling-air supplying unit that supplies cooling air to the combustion chamber along an inner wall surface, and a contraction member arranged along a circumferential direction on the inner wall surface in a downstream of a flow direction of combustion gas in the combustion chamber are provided. The contraction member is provided in a predetermined area in the circumferential direction excluding penetrating portions, which do not disturb the flow of cooling air. Accordingly, in an area where the contraction member is provided in the combustion chamber, the flow of cooling air is disturbed by the contraction member so that cooling air flows toward a central part. Furthermore, a mixing promotion effect by the disturbance can be expected with respect to cooling air flowing in from a downstream of the contraction member. Therefore, cooling air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby enabling to suppress generation of carbon monoxide and unburned hydrocarbon. On the other hand, in an area where the penetrating portions are provided, the flow of cooling air is not disturbed and cooling air flows along the inner wall surface. Accordingly, abnormal combustion of unburned premixed gas can be prevented, and the instability of swirl can be avoided by the presence of the penetrating portions. As a result, generation of unstable combustion can be suppressed.

DESCRIPTION OF EMBODIMENTS

Exemplary embodiments of a gas turbine combustor and a gas turbine according to the present invention will be explained below in detail with reference to the accompanying drawings. The present invention is not limited to the embodiments.

First Embodiment

FIG. 1is a schematic diagram of inside of a transition piece in a gas turbine combustor according to a first embodiment of the present invention,FIG. 2is a cross-sectional view along a line II-II inFIG. 1,FIG. 3is a cross-sectional view along a line III-III inFIG. 2,FIG. 4is a graph representing a heat rate at an axial-direction position in the gas turbine combustor according to the first embodiment, andFIG. 5is a schematic diagram of a gas turbine according to the first embodiment.

As shown inFIG. 5, the gas turbine according to the first embodiment includes a compressor11, a combustor12, and a turbine13. A generator (not shown) is connected to the gas turbine13so that power can be generated.

The compressor11includes an air inlet21that takes in air, and in the compressor11, a plurality of compressor vanes23and rotor blades24are arranged alternately in a longitudinal direction (an axial direction of a rotor32described later) in a compressor casing22, and a bleed air chamber25is provided outside thereof. The combustor12supplies fuel to compressed air compressed by the compressor11to burn fuel by ignition. In the turbine13, a plurality of nozzles27and rotor blades28are arranged alternately in the longitudinal direction (the axial direction of the rotor32described later) in a turbine casing26. An exhaust chamber30is arranged on a downstream side of the turbine casing26through penetrating portions an exhaust casing29, and the exhaust chamber30includes an exhaust diffuser31connected to the turbine13.

The rotor (turbine shaft)32is positioned to penetrate the center of the compressor11, the combustor12, the turbine13, and the exhaust chamber30. An end of the rotor32on a side of the compressor11is rotatably supported by a bearing33, and the other end on a side of the exhaust chamber30is rotatably supported by a bearing34. A plurality of disks on which the respective rotor blades24are mounted are overlapped and fixed to the rotor32in the compressor11, and a plurality of disks on which the respective rotor blade28are mounted are overlapped and fixed to the rotor32in the turbine13. A drive shaft of a generator (not shown) is connected to the end of the rotor32on a side of the exhaust chamber30.

In the gas turbine, the compressor casing22of the compressor11is supported by a leg35, the turbine casing26of the turbine13is supported by a leg36, and the exhaust chamber30is supported by a leg37.

Accordingly, air taken in from the air inlet21of the compressor11is compressed while passing through the compressor vanes23and the rotor blades24so as to become high-temperature and high-pressure compressed air. In the combustor12, predetermined fuel is supplied to the compressed air to burn. High-temperature and high-pressure combustion gas, which is a working fluid generated by the combustor12, passes through the nozzles27and the rotor blades28that constitute the turbine13to rotate the rotor32, thereby driving the generator connected to the rotor32. Meanwhile, the energy of flue gas (combustion gas) is converted to a pressure by the exhaust diffuser31in the exhaust chamber30, and is decelerated and discharged to the atmosphere.

In the combustor12according to the first embodiment described above, as shown inFIG. 1, an inner cylinder42is supported in an outer casing41with a predetermined gap, and a transition piece43is connected to an apical end of the inner cylinder42to constitute a combustor casing. A pilot nozzle44is arranged at the center of the inner cylinder42, and a plurality of main fuel nozzles (premixing nozzles)45are arranged to surround the pilot nozzle44on an inner periphery of the inner cylinder42in a circumferential direction thereof. A pilot cone46is mounted on an apical end of the pilot nozzle44. A plurality of top hat nozzles47are arranged on an inner periphery of the outer casing41along the circumferential direction thereof.

More specifically, an outer casing lid52is attached firmly to a base end of an outer casing body51and fastened by a plurality of fastening bolts53to constitute the outer casing41. A base end of the inner cylinder42is fitted to the outer casing lid52so as to form an air passage54between the outer casing lid52and the inner cylinder42. In the inner cylinder42, the pilot nozzle44is arranged at the center of the inner cylinder42, the main fuel nozzles45are arranged to surround the pilot nozzle44, and the apical ends of the respective main fuel nozzles45are connected to a main burner55.

A top hat part56is fitted to the outer casing lid52and is fastened by a plurality of fastening bolts57. The top hat nozzle47described above is provided in the top hat part56. That is, a fuel cavity58is formed in a base end of the top hat part56along the circumferential direction, a plurality of fuel passages59are formed from the fuel cavity58toward the apical end, and an injection port60is connected to an apical end of each of the fuel passages59.

A pilot fuel line (not shown) is then connected to a fuel port61of the pilot nozzle44, a main fuel line is connected to a fuel port62of the main fuel nozzle45, and a top-hat fuel line is connected to a fuel port63of the top hat nozzle47.

Furthermore, there are formed a plurality of openings64that take in high-pressure air from outside and cool the high-pressure air by causing the high-pressure air to flow along the inner periphery of the inner cylinder42as film air on an outer periphery of the inner cylinder42.

In the first embodiment, a combustion chamber of the present invention is constituted by the inner cylinder42and the transition piece43, a combustion high-pressure-air supplying unit is constituted by the air passage54, a fuel supplying unit according to the present invention is constituted by the pilot nozzle44, the main fuel nozzle45, and the top hat nozzle47, and a cooling-air supplying unit according to the present invention is constituted by the openings64.

Accordingly, when airflow of high-temperature and high-pressure compressed air flows into the air passage54, the compressed air is mixed with fuel injected from the top hat nozzle47, and an air-fuel mixture flows into the inner cylinder42. In the inner cylinder42, the air-fuel mixture is mixed with fuel injected from the main fuel nozzle45by the main burner55, and becomes a swirling current of premixed gas to flow into the transition piece43. The air-fuel mixture is then mixed with fuel injected from the pilot nozzle44, burned by being ignited by a pilot burner (not shown) so as to become combustion gas, and ejected into the transition piece43. At this time, a part of the combustion gas is ejected to diffuse in a surrounding area in the transition piece43with flame, and the combustion gas is ignited by premixed gas flowing from the respective main fuel nozzles45into the transition piece43and burns. That is, flame-holding for performing stable combustion of lean premixed fuel from the main fuel nozzle45can be performed by diffused flame of the pilot fuel injected from the pilot nozzle44. Further, airflow of high-temperature and high-pressure compressed air is taken in from the openings64and flows along the inner wall surfaces of the inner cylinder42and the transition piece43to be cooled. Accordingly, a temperature increase of the inner cylinder42and the transition piece43due to combustion gas can be suppressed.

As shown inFIGS. 1 to 3, in the combustor12according to the first embodiment configured as described above, three contraction members71,72, and73are arranged along a circumferential direction of the inner cylinder42on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder42. The contraction members71,72, and73are provided in a predetermined area in the circumferential direction excluding penetrating portions74,75, and76, which do not disturb the flow of film air (cooling air).

More specifically, the respective contraction members71,72, and73have substantially the same shape, with a cross section thereof being an L-shape. A base end of each of these contraction members is fixed to the inner wall surface of the inner cylinder42by welding (or a bolt)77, and an apical end thereof is supported by a support member78with a predetermined gap from the inner wall surface of the inner cylinder42. Therefore, in the respective contraction members71,72, and73, a guide surface inclined by a predetermined angle θ is formed to cause film air flowing on the inner wall surface of the inner cylinder42to flow toward the central part of the inner cylinder42. The contraction members71,72, and73respectively include corner portions71aand71b,72aand72b,73aand73bprotruding toward the central part of the inner cylinder42.

Meanwhile, the penetrating portions74,75, and76are positioned between the respective contraction members71,72, and73, and have substantially the same shape. That is, the contraction members71,72, and73are provided through the penetrating portions74,75, and76, namely, the contraction members71,72, and73and the penetrating portions74,75, and76are divided in plural (three in the present embodiment) in the circumferential direction, and are arranged alternately in the circumferential direction. In this case, the contraction members71,72, and73are provided at asymmetric positions with respect to the circumferential direction on the inner wall surface of the inner cylinder42. However, the contraction members71,72, and73do not need to be provided at asymmetric positions in the circumferential direction and can be provided at symmetric positions.

Therefore, in the inner cylinder42, combustion gas flows in the central part, and film air flows along the inner wall surface of the outer periphery. At this time, in the inner cylinder42, in an area where the contraction members71,72, and73are provided, the flow of combustion gas is disturbed so that film air flows from the contraction members71,72, and73toward the central part. At the same time, the flow of cooling air flowing in from the downstream of the contraction members71,72, and73is disturbed by the contraction members71,72, and73. Therefore, film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon.

Furthermore, in the inner cylinder42, film air and combustion gas are easily mixed with each other in the area where the contraction members71,72, and73are provided. On the other hand, in an area where the contraction members71,72, and73are not provided and only the penetrating portions74,75, and76are provided, the flow of film air is not disturbed and the film air flows along the inner wall surface. Therefore, abnormal combustion of unburned premixed gas is prevented, and the instability of swirl is avoided by the presence of the penetrating portions74,75, and76, thereby suppressing generation of unstable combustion.

In this case, because the respective contraction members71,72, and73are divided in plural, and they include the corner portions71aand71b,72aand72b,73aand73b, respectively, film air, the flow of which has been disturbed by the contraction members71,72, and73, also causes effects on film air passing through the penetrating portions74,75, and76, and thus generation of carbon monoxide and unburned hydrocarbon and an increase in combustion gas temperature are effectively suppressed.

FIG. 4is a graph representing a heat rate with respect to a distance from a base end to an apical end in the combustor12. As shown inFIG. 4, in a conventional combustor in which any contraction member is not provided, as shown by the dotted line inFIG. 4, the heat rate becomes highest in the middle part. In a conventional combustor in which a contraction member in a ring shape is provided at a position L, as shown by the solid line inFIG. 4, the heat rate excessively increases immediately after the position of the contraction member. On the other hand, in the combustor12in which the contraction members71,72, and73according to the first embodiment are provided, as shown by the one-dot chain line inFIG. 4, the highest value of the heat rate is lower than that of the above conventional combustor.

Furthermore, the contraction members71,72, and73are provided at asymmetric positions with respect to the circumferential direction on the inner wall surface of the inner cylinder42, the flame pattern becomes unbalanced with respect to the circumferential direction, and the length of a flame sheet in an axial direction in this portion changes. As a result, the temperature distribution in an area where the contraction members71,72, and73are provided and in an area where the penetrating portions74,75, and76are provided changes along with the circumferential direction, and an excitation force that generates unstable vibration in the axial direction of the combustor is reduced.

Meanwhile, because the flame has an asymmetrical distribution with respect to the circumferential direction, generation of a vibration mode in which “+” and “−” are inverted is suppressed in a vibration mode in the cross section.

In this case, the contraction members71,72, and73are provided at asymmetric positions in the circumferential direction. The asymmetric positions with respect to the circumferential direction are positions at which a diameter line (a node at which the phase is inverted) cannot be drawn in the vibration mode in which a cross section of the inner cylinder42is uniformly divided into even numbers. In this explanation, it is set at a position where the contraction members71,72, and73are not overlapped in the circumferential direction and are not in point symmetry with respect to the center of the inner cylinder42. That is, in the present embodiment, the contraction members71,72, and73(the penetrating portions74,75, and76) are set at positions away from each other by 120 degrees in the circumferential direction.

As described above, in the gas turbine combustor according to the first embodiment, the air passage54that supplies combustion high-pressure air, the pilot nozzle44, the main fuel nozzle45, and the top hat nozzle47that supply fuel, and the openings64that supplies film air (cooling air) are provided with respect to the inner cylinder42. The contraction members71,72, and73are arranged along the circumferential direction on the inner wall surface in the downstream of the flow direction of combustion gas in the inner cylinder42, and provided in a predetermined area in the circumferential direction excluding the penetrating portions74,75, and76, which do not disturb the flow of film air.

Accordingly, in the inner cylinder42, in the area where the contraction members71,72, and73are provided, the flow of film air is disturbed by the contraction members71,72, and73so that film air flows toward a central part. At the same time, the flow of cooling air flowing from the downstream of the contraction members71,72, and73is also disturbed by the contraction members71,72, and73, and thus cooling air is mixed with high-temperature combustion gas, thereby enabling to promote a combustion reaction and to suppress generation of carbon monoxide and unburned hydrocarbon. On the other hand, in the area where the penetrating portions74,75, and76are provided, because the film air flows along the inner wall surface without being disturbed, abnormal combustion of unburned premixed gas can be prevented, and the instability of swirl can be avoided by the presence of the penetrating portions74,75, and76. As a result, generation of unstable combustion can be suppressed.

In the gas turbine combustor according to the first embodiment, the contraction members71,72, and73are divided into three through the penetrating portions74,75, and76and arranged in the circumferential direction. Therefore, the gap between the contraction members71,72, and73and the penetrating portions74,75, and76becomes short, thereby enabling to prevent abnormal combustion of unburned premixed gas and to avoid the instability of swirl by the presence of the penetrating portions74,75, and76.

In the gas turbine combustor according to the first embodiment, the contraction members71,72, and73are provided at the asymmetric positions with respect to the circumferential direction on the inner wall surface of the inner cylinder42. Therefore, the flame pattern becomes unbalanced with respect to the circumferential direction, and the temperature distribution in the inner cylinder42changes along with the circumferential direction, thereby enabling to suppress generation of a vibration mode and to suppress generation of unstable combustion.

Furthermore, in the gas turbine combustor according to the first embodiment, the contraction members71,72, and73respectively include the corner portions71aand71b,72aand72b, and73aand73bprotruding toward the central part of the combustion chamber. Accordingly, film air generates swirl at the corner portions71aand71b,72aand72b, and73aand73bof the contraction members71,72, and73, thereby promoting mixing of combustion gas with cooling air.

In the first embodiment, the contraction members71,72, and73have the same shape and the penetrating portions74,75, and76also have the same shape, and these elements are arranged with an equal gap in the circumferential direction. However, these elements can be also arranged asymmetrically by changing the circumferential length of the contraction members71,72, and73and the penetrating portions74,75, and76, by changing a protruding amount of the contraction members71,72, and73toward the central part, or by changing the gap in the circumferential direction.

Second Embodiment

FIG. 6is a schematic diagram of a cross section of a gas turbine combustor according to a second embodiment of the present invention. Members having functions identical to those explained in the above embodiment are denoted by like reference signs and redundant explanations thereof will be omitted.

In the second embodiment, as shown inFIG. 6, contraction members81and82are arranged along a circumferential direction of the inner cylinder42on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder42. The contraction members81and82are provided in a predetermined area in the circumferential direction excluding penetrating portions83and84, which do not disturb the flow of film air (cooling air).

That is, the contraction members81and82respectively have a different length in the circumferential direction, and include corner portions81aand81b,82aand82b, respectively, that protrude toward a central part of the inner cylinder42. On the other hand, the penetrating portions83and84are positioned between the respective contraction members81and82, and have a different length in the circumferential direction. That is, the contraction members81and82are divided in plural through the penetrating portions83and84and arranged in the circumferential direction. In this case, the contraction members81and82and the penetrating portions83and84are provided at the asymmetric positions with respect to the circumferential direction on the inner wall surface of the inner cylinder42.

Accordingly, in the inner cylinder42, combustion gas flows in the central part, and film air flows along the inner wall surface of an outer periphery. At this time, in the inner cylinder42, in an area where the contraction members81and82are provided, the flow of film air is disturbed by the contraction members81and82so that the film air flows toward the central part. Therefore, the film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon.

In the inner cylinder42, film air and combustion gas are easily mixed with each other in the area where the contraction members81and82are provided. On the other hand, in an area where the contraction members81and82are not provided and only the penetrating portions83and84are provided, the flow of film air is not disturbed and the film air flows along the inner wall surface. Therefore, abnormal combustion of unburned premixed gas is prevented, and the instability of swirl is avoided by the presence of the penetrating portions83and84, thereby suppressing generation of unstable combustion.

Furthermore, the contraction members81and82and the penetrating portions83and84are provided asymmetrically with respect to the circumferential direction on the inner wall surface of the inner cylinder42, a flame pattern becomes unbalanced with respect to the circumferential direction, and the length of a flame sheet in an axial direction in this portion changes. Therefore, the temperature distribution in the area where the contraction members81and82are provided and in the area where the penetrating portions83and84are provided changes along with the circumferential direction, and an excitation force that generates unstable vibration in the axial direction of the combustor is reduced.

As described above, in the gas turbine combustor according to the second embodiment, the two contraction members81and82are arranged along the circumferential direction on the inner wall surface of the inner cylinder42in the downstream of the flow direction of combustion gas, and the contraction members81and82are provided in a predetermined area in the circumferential direction excluding the penetrating portions83and84, which do not disturb the flow of film air.

Accordingly, the flow of film air is disturbed by the contraction members81and82and film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon. Meanwhile, abnormal combustion of unburned premixed gas is prevented by the penetrating portions83and84, and the instability of swirl is avoided by the presence of the penetrating portions83and84to suppress generation of unstable combustion.

Third Embodiment

FIG. 7is a schematic diagram of a cross section of a gas turbine combustor according to a third embodiment of the present invention. Members having functions identical to those explained in the above embodiments are denoted by like reference signs and redundant explanations thereof will be omitted.

In the third embodiment, as shown inFIG. 7, contraction members91to98are arranged along a circumferential direction of the inner cylinder42on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder42. The contraction members91to98are provided in a predetermined area in the circumferential direction excluding penetrating portions101to108, which do not disturb the flow of film air (cooling air).

That is, the respective contraction members91to98have the same shape, the penetrating portions101to108also have the same shape, and these elements are provided with an equal gap in the circumferential direction. These elements can be provided at asymmetric positions with respect to the circumferential direction, by changing the shape, length, arrangement or the like as required.

Accordingly, in the inner cylinder42, combustion gas flows in the central part, and film air flows along the inner wall surface of an outer periphery. At this time, in the inner cylinder42, in an area where the contraction members91to98are provided, the flow of film air is disturbed by the contraction members91to98so that the film air flows toward the central part. Therefore, film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon.

In the inner cylinder42, film air and combustion gas are easily mixed with each other in the area where the contraction members91to98are provided. On the other hand, in an area where the contraction members91to98are not provided and only the penetrating portions101to108are provided, the flow of film air is not disturbed and the film air flows along the inner wall surface. Therefore, abnormal combustion of unburned premixed gas is prevented, and the instability of swirl is avoided by the presence of the penetrating portions101to108, thereby suppressing generation of unstable combustion.

As described above, in the gas turbine combustor according to the third embodiment, the eight contraction members91to98are arranged along the circumferential direction on the inner wall surface of the inner cylinder42in the downstream of the flow direction of combustion gas, and the contraction members91to98are provided in a predetermined area in the circumferential direction excluding the penetrating portions101to108, which do not disturb the flow of film air.

Accordingly, the flow of film air is disturbed by the contraction members91to98and film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon. Meanwhile, abnormal combustion of unburned premixed gas is prevented by the penetrating portions101to108, and the instability of swirl is avoided by the presence of the penetrating portions101to108. As a result, generation of unstable combustion can be suppressed.

Fourth Embodiment

FIG. 8is a schematic diagram of inside of a transition piece in a gas turbine combustor according to a fourth embodiment of the present invention, andFIG. 9is a cross-sectional view along a line IX-IX inFIG. 8. Members having functions identical to those explained in the above embodiments are denoted by like reference signs and redundant explanations thereof will be omitted.

In the fourth embodiment, as shown inFIGS. 8 and 9, three contraction members111,112, and113are arranged along a circumferential direction of the inner cylinder42on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder42. The contraction members111,112, and113are provided in a predetermined area in the circumferential direction excluding penetrating portions114,115, and116, which do not disturb the flow of film air (cooling air).

That is, the respective contraction members111,112, and113have substantially the same length in the circumferential direction, and are provided while being shifted in the flow direction of combustion gas, and are provided while also being shifted in the circumferential direction. In this case, the three contraction members111,112, and113are arranged so that a part thereof overlaps on each other with respect to the flow direction of combustion gas. On the other hand, the penetrating portions114,115, and116are shifted in the circumferential direction of the respective contraction members111,112, and113and positioned at the same position with respect to the flow direction of combustion gas, with the circumferential length thereof being substantially the same. In this case, the contraction members111,112, and113and the penetrating portions114,115, and116are provided at asymmetric positions with respect to the circumferential direction on the inner wall surface of the inner cylinder42.

Accordingly, in the inner cylinder42, combustion gas flows in the central part, and film air flows along the inner wall surface of an outer periphery. At this time, in the inner cylinder42, in an area where the contraction members111,112, and113are provided, the flow of film air is disturbed by the contraction members111,112, and113so that the film air flows toward the central part. Therefore, film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon.

In the inner cylinder42, film air and combustion gas are easily mixed with each other in the area where the contraction members111,112, and113are provided. On the other hand, in an area where the contraction members111,112, and113are not provided and only the penetrating portions114,115, and116are provided, the flow of film air flows along the inner wall surface without being disturbed. Therefore, abnormal combustion of unburned premixed gas is prevented, and the instability of swirl is avoided by the presence of the penetrating portions114,115, and116, thereby suppressing generation of unstable combustion.

Furthermore, the contraction members111,112, and113and the penetrating portions114,115, and116are provided asymmetrically with respect to the circumferential direction on the inner wall surface of the inner cylinder42, a flame pattern becomes unbalanced with respect to the circumferential direction, and the length of a flame sheet in an axial direction in this portion changes. Therefore, the temperature distribution in the area where the contraction members111,112, and113are provided and in an area where the penetrating portions114,115, and116are provided changes along with the circumferential direction, and an excitation force that generates unstable vibration in the axial direction of the combustor is reduced.

As described above, in the gas turbine combustor according to the fourth embodiment, the three contraction members111,112, and113are arranged along the circumferential direction on the inner wall surface of the inner cylinder42in the downstream of the flow direction of combustion gas, and the contraction members111,112, and113are provided while being shifted in the circumferential direction and in the axial direction of the inner cylinder42, and the contraction members111,112, and113are provided in a predetermined area in the circumferential direction excluding the penetrating portions114,115, and116, which do not disturb the flow of film air.

Accordingly, the flow of film air is disturbed by the contraction members111,112, and113and film air is mixed with high-temperature combustion gas to promote a combustion reaction, thereby suppressing generation of carbon monoxide and unburned hydrocarbon. Meanwhile, abnormal combustion of unburned premixed gas is prevented by the penetrating portions101to108, and the instability of swirl is avoided by the presence of the penetrating portions114,115, and116to suppress generation of unstable combustion.

In the respective embodiments described above, the contraction members are configured to have a shape with corner portions protruding toward the central part of the combustion chamber; however, the shape of the contraction member is not limited thereto. For example, a semicircular board can be fixed to the inner wall surface of the combustion chamber, and the contraction member does not particularly need to have a shape having corner portions. Furthermore, the position at which the contraction member is arranged is not limited to the inner cylinder42positioned immediately below the respective nozzles44,45, and47, and the contraction member can be provided in the transition piece43, and the arrangement is not limited to be symmetrical and asymmetrical.

INDUSTRIAL APPLICABILITY

According to the gas turbine combustor and gas turbine of the present invention, a contraction member is provided in a predetermined area in a circumferential direction excluding penetrating portions, which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress generation of unstable combustion. Accordingly, the gas turbine combustor and the gas turbine can be also applied to any types of combustors and gas turbines.

REFERENCE SIGNS LIST