JP6619307B2 - Gas turbine combustor - Google Patents

Description

  The present invention relates to a structure of a gas turbine combustor, and more particularly to a technique effective for suppressing deformation caused by vibration of an outlet portion of a flow sleeve.

  The transition piece of the gas turbine combustor has a flow sleeve around it because high-temperature combustion gas flows inside, so that the cooling air discharged from the compressor flows through the flow path between the transition piece and the flow sleeve. It is in a shape enclosed in a flow sleeve. In the flow sleeve, in order to enhance the cooling effect of the transition piece by the cooling air, impingement holes (cooling holes) are provided on the back side and the abdomen side of the transition piece outlet side.

  One form of damage that is a concern in the flow sleeve is a crack associated with vibration. An example of a crack is due to the left and right split shape of the flow sleeve outlet and the fluid excitation of the discharge air and combustion gas from the compressor, and the free end of the flow sleeve vibrates in a cantilevered state. There is a concern about the possibility of a phenomenon in which a fine crack is generated and grows from a metal surface or the like due to repeated vibrations, leading to fracture. An effective countermeasure against damage due to vibration is stress reduction, and it is desirable to reduce the vibration stress by changing the shape of the flow sleeve or improving the rigidity.

  As a background art in this technical field, for example, there is a technique such as Patent Document 1. Patent Document 1 proposes a structure in which the cooling air flow is made uniform over the entire circumference by widening the back side and narrowing the abdomen side of the convection cooling flow path provided between the transition piece and the flow sleeve. ing.

  According to the gas turbine combustor disclosed in Patent Document 1, the transition piece can be efficiently cooled to a metal temperature that is uniform over the entire circumference, and thermal deformation due to a temperature difference between the back side portion and the ventral side portion can be suppressed. It is said.

JP-A-1-167530

  In recent years, with the improvement in performance of gas turbines, the design to increase the pressure ratio of the compressor while simultaneously burning at a high temperature is becoming mainstream, and it is necessary to further reduce the load acting on the transition piece and the flow sleeve. The above Patent Document 1 does not aim at reducing the stress of the flow sleeve, and a new structure is required.

  Accordingly, an object of the present invention is to provide a highly reliable gas turbine combustor that has a relatively simple structure, suppresses deformation due to vibration of the end of the flow sleeve, and can prevent the flow sleeve from cracking or breaking. It is to provide.

In order to solve the above-described problems, the present invention provides a transition piece that guides combustion gas from a combustor to a turbine, and a compressor provided between the transition piece that is provided around the transition piece and encloses the transition piece. And a flow sleeve that forms a flow path for cooling air discharged from the turbine, wherein the flow sleeve is an impingement hole that serves as an introduction hole for the cooling air in the vicinity of the end on the turbine side. A plurality of divided parts are integrated by a connecting tie piece, and an end part on the turbine side is reinforced by an all-around integral bell mouth, and an outlet part on the turbine side of the transition piece is provided. A frame is provided, and the flow sleeve has a flow sleeve support, a hinge, and a frame support on the back side. Coupled to the frame by chromatography preparative, ventral inner peripheral side flow sleeve support, the inner peripheral side hinge that is connected to the frame by the inner peripheral side frame support, characterized in that it is fixed to the transition piece .

  According to the present invention, a highly reliable gas turbine combustor capable of suppressing deformation caused by vibration of the end of the flow sleeve and preventing the flow sleeve from cracking or breaking with a relatively simple structure is realized. be able to.

  Problems, configurations, and effects other than those described above will be clarified by the following description of embodiments.

It is a figure which shows the structural example of a general gas turbine. It is a figure which shows the structural example of the right-and-left division | segmentation type | mold flow sleeve which has the conventional left-right division | segmentation bell mouth. In the structural example of FIG. 2, it is the figure which modeled the deformation | transformation which arises in the left-right in-phase by vibration on the inner peripheral side and outer peripheral side of a right-and-left division type flow sleeve. In the structural example of FIG. 2, it is the figure which modeled the deformation | transformation which arises in a right-and-left different phase by vibration on the inner peripheral side and outer peripheral side of a right-and-left division type flow sleeve. It is a figure which shows the right-and-left division | segmentation type | mold flow sleeve which concerns on one Embodiment of this invention. It is a figure which shows the up-and-down division | segmentation type | mold flow sleeve which concerns on one Embodiment of this invention. It is a figure which shows the structural example of the conventional transition piece and flow sleeve. It is a figure which shows the structure of the transition piece and flow sleeve which concern on one Embodiment of this invention. It is a figure which shows the structural example of the right-and-left division | segmentation type | mold flow sleeve which has the conventional left-right division | segmentation bell mouth. It is a figure which shows the right-and-left division | segmentation type | mold flow sleeve which concerns on one Embodiment of this invention. It is a figure which shows the up-and-down division type flow sleeve concerning one embodiment of the present invention. It is a figure which shows the structure of the transition piece and flow sleeve which concern on one Embodiment of this invention. It is a figure which shows the perimeter integrated bellmouth which concerns on one Embodiment of this invention. It is a figure which shows the A-A 'cross section in FIG. 13A. It is a figure which shows the flow of the cooling air between a transition piece and a flow sleeve.

  Embodiments of the present invention will be described below with reference to the drawings. In the drawings, the same components are denoted by the same reference numerals, and detailed description of the overlapping portions is omitted.

  First, a gas turbine that is an object of the present invention will be described with reference to FIGS. 1 to 4 and FIG. 14. FIG. 1 is a cross-sectional view showing an example of the structure of a general gas turbine. FIG. 2 is a perspective view showing a flow sleeve provided around a transition piece that guides combustion gas from a combustor of a gas turbine to the turbine, and shows an example of a structure of a left and right split type flow sleeve having a conventional left and right split bell mouth. Yes. FIG. 14 is a diagram showing the flow of cooling air between the transition piece and the flow sleeve. 3 and 4 show the deformation that occurs in the left and right in-phase due to vibration on the inner peripheral side (belly side) and the outer peripheral side (back side) of the left and right split type flow sleeve in the structural example of FIG. FIG.

  As shown in FIG. 1, the gas turbine is roughly composed of a compressor 1, a combustor 2, and a turbine 3. The compressor 1 adiabatically compresses air sucked from the atmosphere as a working fluid, and the combustor 2 mixes and burns fuel with the compressed air supplied from the compressor 1 to generate high-temperature and high-pressure combustion gas, and the turbine. 3 generates rotational power when the combustion gas introduced from the combustor 2 expands. Exhaust gas from the turbine 3 is released into the atmosphere.

  Between the combustor 2 and the turbine 3, a transition piece (not shown) that guides combustion gas from the combustor 2 to the turbine 3 is provided. The flow sleeve of FIG. 2 is provided around the transition piece. This flow sleeve is configured by abutting two divided flow sleeves 4 and 4 ′, which are two divided portions, with a combustor transition piece (not shown) through which combustion gas flows along the flow direction 9. Enclose.

  The abutting portions of the inner peripheral side (abdominal side) and the outer peripheral side (back side) of the left and right divided flow sleeves 4 and 4 ′ are connected by a left and right connection tie piece 10. Left and right split bell mouths 5 and 5 ′ are provided at the ends of the left and right split flow sleeves 4 and 4 ′ on the turbine 3 side in order to reinforce the ends. Further, in the vicinity of the end of the left and right divided flow sleeves 4 and 4 ′ on the turbine 3 side, impingement holes (cooling) serving as cooling air introduction holes on the inner peripheral side (belly side) and the outer peripheral side (back side), respectively. A plurality of holes 6 are provided. FIG. 2 shows an example in which a plurality of impingement holes (cooling holes) 6 are provided on both side surfaces of the flow sleeve.

  As shown in FIG. 14, the cooling air 24 discharged from the compressor is taken in between the flow sleeve 4 and the transition piece 15 through the impingement hole (cooling hole) 6 provided in the flow sleeve 4, and the flow sleeve The transition piece 15 is cooled by the cooling air 24 flowing through the flow path of the cooling air formed between the transition piece 15 and the transition piece 15.

  In the conventional gas turbine combustor, as shown in FIG. 2, the end of the flow sleeve 4 on the turbine side is reinforced by the left and right divided bell mouths 5 and 5 ′. In the portion, the left and right split bell mouths 5 and 5 'are not connected to each other, and each has a free end. Further, in the vicinity of the end of the left and right divided flow sleeves 4 and 4 ′ on the turbine side, there may be a portion that is not connected by the left and right connection tie pieces 10.

  As described above, the free end of the flow sleeve vibrates in a cantilevered state due to fluid excitation of discharge air and combustion gas from the compressor. This vibration varies depending on the shape and size of the flow sleeve and the conditions such as the flow rate and flow rate of the discharge air and combustion gas from the compressor, but both the outer peripheral side 7 and the inner peripheral side 8 of the flow sleeve as shown in FIG. There are cases where the left and right in-phase vibrates and deforms, and as shown in FIG. 4, the outer peripheral side 7 and the inner peripheral side 8 of the flow sleeve both vibrate and deform in left and right different phases. In any case, the repetition of this vibration may generate and grow a fine crack from the metal surface or the like, leading to breakage.

  Next, the flow sleeve in the present embodiment will be described with reference to FIGS. 5 and 13A and 13B. FIG. 5 is a perspective view showing a flow sleeve of the present embodiment, and is a view corresponding to FIG. 2 showing a conventional flow sleeve. FIG. 13A is a front view of the all-around integral bell mouth 12 in FIG. 5, and FIG. 13B shows a cross-section along A-A ′ in FIG. 13A.

  The flow sleeve of the present embodiment is similar to the conventional flow sleeve shown in FIG. 2, and the respective butted portions of the inner peripheral side (abdominal side) and the outer peripheral side (back side) of the left and right divided flow sleeves 4 and 4 ′ are The left and right connecting tie pieces 10 are connected to each other. Impingement holes (cooling holes) 6 serving as cooling air introduction holes are provided on the inner peripheral side (abdominal side) and the outer peripheral side (back side) of the left and right divided flow sleeves 4 and 4 ′ in the vicinity of the end of the turbine 3. A plurality of points are the same as in FIG.

  In the flow sleeve of FIG. 2, the end of the left and right divided flow sleeves 4 and 4 ′ on the turbine 3 side is reinforced by the left and right divided bell mouths 5 and 5 ′, whereas the flow sleeve of this embodiment has the left and right divided flow. 2 is different from the flow sleeve of FIG. 2 in that the ends of the sleeves 4 and 4 ′ on the turbine 3 side are reinforced with the all-around integral bell mouth 12.

  As shown in FIG. 5, the bell mouth, which has conventionally been divided into left and right parts, is integrated around the entire circumference, thereby improving the rigidity of the end of the flow sleeve on the turbine side (the end on the outlet side) and allowing it to be a free end. The structure can be eliminated and cantilever-like deformation can be suppressed. Thereby, the repeated stress accompanying vibration can be reduced, and deformation and damage of the flow sleeve can be prevented.

  The all-round integrated bell mouth 12 is preferably formed as a single piece using a material having high rigidity such as SUS material.

  With reference to FIG. 6, the flow sleeve of Example 2 is demonstrated. FIG. 6 is a perspective view showing the flow sleeve of the present embodiment, and corresponds to FIG. 5 of the first embodiment. As shown in FIG. 6, the flow sleeve of the present embodiment is formed by abutting upper and lower divided flow sleeves 11, 11 ′ with each other and connecting the abutting portions with upper and lower connection tie pieces 13.

  Impingement holes (cooling holes) 6 serving as cooling air introduction holes are provided on the inner peripheral side (belly side) and the outer peripheral side (back side) of the upper and lower divided flow sleeves 11 and 11 ′ in the vicinity of the turbine 3 side end. A plurality of points are the same as in FIG.

  Also in the upper / lower split type flow sleeve of the present embodiment, the end portions on the turbine 3 side of the upper / lower split flow sleeves 11, 11 ′ are reinforced by the all-around integral bell mouth 12. Accordingly, the rigidity of the end portion on the turbine side (the end portion on the outlet side) of the flow sleeve is improved and the free end is provided as in the case of the flow sleeve on the left and right division side to which the all-round integrated bell mouth 12 of the first embodiment is applied. Can be eliminated, and cantilever-like deformation can be suppressed.

  Note that the upper and lower divided flow sleeves 11 and 11 ′ of FIG. 6 have relatively improved rigidity of the plate thickness with respect to the length compared to the left and right divided flow sleeves 4 and 4 ′ of FIG. On the other hand, there is an advantage that cracks and breakage are less likely to occur.

  With reference to FIG. 7 and FIG. 8, the flow sleeve and transition piece of Example 3 are demonstrated. FIG. 7 shows an example of a conventional method of fixing the flow sleeve to the transition piece for comparison. FIG. 8 shows a method of fixing the flow sleeve to the transition piece of this embodiment.

  In the conventional gas turbine combustor, as shown in FIG. 7, the flow sleeve support 19 provided on the back side surface (upper surface) of the flow sleeve 4 is provided at the outlet portion of the transition piece 15 via the hinge 18 and the frame support 17. It is fixed by connecting to the frame 16. Since the flow sleeve 4 is supported only on the upper surface side, the flow sleeve 4 as a whole vibrates up and down due to fluid excitation such as discharge air and combustion gas from the compressor, and the free end of the flow sleeve is in a cantilever state. Vibrate.

  Therefore, in the structure of this embodiment, as shown in FIG. 8, in addition to supporting the flow sleeve 4 on the upper surface side as in the prior art, the inner peripheral flow provided on the ventral side surface (lower surface) of the flow sleeve 4 is used. The sleeve support 23 is fixed by being connected to the frame 16 at the outlet of the transition piece 15 via the inner peripheral hinge 22 and the inner peripheral frame support 21.

  Thereby, vibration generated in the flow sleeve 4, particularly vibration generated on the abdominal side surface (lower surface) of the flow sleeve 4, can be suppressed, and occurrence of cracks or breakage to the flow sleeve 4 can be prevented.

  Note that the fixing method of the present embodiment can be applied to both the left and right divided flow sleeves of the first embodiment and the upper and lower divided flow sleeves of the second embodiment.

  Further, as shown in FIG. 8, in addition to supporting the back side surface (upper surface) and the abdominal side surface (lower surface) of the flow sleeve 4, the flow sleeve 4 may be fixed to the transition piece 15 by the inner peripheral side fixing plate 20.

  Further, in addition to the method for fixing the flow sleeve to the transition piece of the present embodiment, the deformation of the flow sleeve 4 due to vibration is further suppressed by applying the all-round integrated bell mouth described in the first and second embodiments. And the reliability of the gas turbine combustor can be improved.

  With reference to FIG. 9 and FIG. 10, the flow sleeve of Example 4 is demonstrated. FIG. 9 shows an example of a conventional flow sleeve provided with a gusset 14 shown for comparison. FIG. 10 shows a flow sleeve of this embodiment provided with a gusset 14. The gusset is a plate material used as a reinforcing component at a location where a steel plate member is connected.

  FIG. 9 is a form in which a gusset 14 for reinforcing the joint portion of the left and right divided flow sleeves 4 and 4 ′ is added to the flow sleeve described in FIG. 2 of the first embodiment. In the flow sleeve of FIG. 9, the ends are reinforced by the left and right divided bell mouths 5 and 5 ′. The left and right connecting tie pieces 10, the all-round integrated bell mouth 12, and a plurality of gussets 14 provided along the combustion gas flow direction 9 are fixed, and deformation due to vibration of the flow sleeve 4 can be more effectively suppressed.

  With reference to FIG. 11, the flow sleeve of Example 5 is demonstrated. FIG. 11 is a form in which a gusset 14 for reinforcement is added to each of the upper and lower divided flow sleeves 11 and 11 ′ in the upper and lower divided flow sleeve described in FIG. 6 of the second embodiment. A plurality of gussets 14 are provided along the combustion gas flow direction 9. As shown in FIG. 11, the upper and lower divided flow sleeves 11 and 11 ′ are provided with gussets 14 and the ends thereof are reinforced by the all-in-one bell mouth 12 to effectively deform the flow sleeves 11 and 11 ′ due to vibration. Can be suppressed.

  With reference to FIG. 12, the flow sleeve and transition piece of Example 6 are demonstrated. FIG. 12 shows a method of fixing the flow sleeve to the transition piece of this embodiment. FIG. 12 shows the gussets 14 and 14 ′ for reinforcement on the back side surface (upper surface) and the abdominal side surface (lower surface) of the flow sleeve 4 in addition to the method of fixing the flow sleeve to the transition piece described in FIG. It is the form which added.

  In addition to supporting the back side surface (upper surface) and the abdominal side surface (lower surface) of the flow sleeve 4, by providing the flow sleeve 4 with gussets 14 and 14 'for reinforcement, vibration generated in the flow sleeve 4 is suppressed, and the flow sleeve 4 The occurrence of cracks and breaks to 4 can be effectively prevented.

  In addition, each embodiment described in each of the above examples may be used alone, or a plurality of examples may be combined.

  The present invention is not limited to the above-described embodiments, and includes various modifications. For example, the above-described embodiments have been described in detail for easy understanding of the present invention, and are not necessarily limited to those having all the configurations described. Further, a part of the configuration of a certain embodiment can be replaced with the configuration of another embodiment, and the configuration of another embodiment can be added to the configuration of a certain embodiment. Further, it is possible to add, delete, and replace other configurations for a part of the configuration of each embodiment.

DESCRIPTION OF SYMBOLS 1 ... Compressor 2 ... Combustor 3 ... Turbine 4, 4 '... Left-right division | segmentation flow sleeve 5, 5' ... Left-right division | segmentation bell mouth 6 ... Impingement hole (cooling hole)
7 ... Outer peripheral side 8 ... Inner peripheral side 9 ... Combustion gas flow direction 10 ... Left and right connecting tie piece 11, 11 '... Upper and lower split flow sleeve 12 ... All-round integrated bell mouth 13 ... Upper and lower connecting tie piece 14, 14' ... Gusset 15 ... Transition Piece 16 ... Frame 17 ... Frame support 18 ... Hinge 19 ... Flow sleeve support 20 ... Inner peripheral side fixing plate 21 ... Inner peripheral side frame support 22 ... Inner peripheral side hinge 23 ... Inner peripheral side flow sleeve support 24 ... Cooling air.

Claims (9)

A transition piece for directing combustion gas from the combustor to the turbine;
A gas sleeve combustor comprising: a flow sleeve provided around the transition piece, and enclosing the transition piece and forming a flow path of cooling air discharged from the compressor between the transition piece and the transition piece; ,
The flow sleeve is provided with an impingement hole serving as an introduction hole for the cooling air in the vicinity of the end on the turbine side,
A plurality of divided parts are integrated by a connecting tie piece, and the end on the turbine side is reinforced with an all-around integral bell mouth ,
A frame is provided at the outlet of the transition piece on the turbine side,
The flow sleeve has a back side connected to the frame by a flow sleeve support, a hinge and a frame support, and a ventral side connected to the frame by an inner flow sleeve support, an inner peripheral hinge and an inner frame support. A gas turbine combustor fixed to the transition piece . A gas turbine combustor according to claim 1,
2. The gas turbine combustor according to claim 1, wherein the flow sleeve is a left and right divided flow sleeve in which two divided parts divided into left and right are integrated by a connecting tie piece. A gas turbine combustor according to claim 2,
A gas turbine combustor characterized in that a connecting portion of the two divided portions is reinforced with a gusset. A gas turbine combustor according to claim 1,
2. The gas turbine combustor according to claim 1, wherein the flow sleeve is a vertically divided flow sleeve in which two divided parts divided vertically are integrated by a connecting tie piece. A gas turbine combustor according to claim 4,
A gas turbine combustor characterized in that each of the two divided portions is reinforced with a gusset. A gas turbine combustor according to claim 1 ,
The gas turbine combustor, wherein the flow sleeve is further fixed to the transition piece by an inner peripheral side fixing plate. A gas turbine combustor according to any one of claims 1 to 6 ,
A plurality of the impingement holes are provided on each of the back side surface and the abdominal side surface of the flow sleeve. A gas turbine combustor according to claim 3 or 5,
The gas turbine combustor, wherein a plurality of the gussets are provided along a flow direction of the combustion gas flowing in the transition piece. A gas turbine combustor according to any one of claims 1 to 8 ,
The gas turbine combustor characterized in that the all-round integrated bell mouth is made of SUS material.

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