Gas turbine

Abstract

A gas turbine includes a rotor that is rotatable about an axis, a casing configured to cover the rotor in a circumferential direction and having an annular space therein, a compressor configured to generate a high pressure of compressed air obtained by compressing external air and send the compressed air into the casing, a plurality of combustors disposed in the casing at equal intervals in the circumferential direction of the rotor and configured to combust the compressed air and fuel taken in from the casing to generate a combustion gas, a turbine driven by the combustion gas, and an air introduction passage defined by a partition plate configured to divide the space in the casing in the circumferential direction of the rotor and an inner circumferential surface of the casing and configured to introduce the compressed air in the casing into the combustor.

What is claimed is: 
     
         1 . A gas turbine comprising:
 a rotor that is rotatable about an axis;   a casing configured to cover the rotor in a circumferential direction and having an annular space therein;   a compressor configured to generate a high pressure of compressed air obtained by compressing external air and send the compressed air into the casing;   a plurality of combustors disposed in the casing at equal intervals in the circumferential direction of the rotor and configured to combust the compressed air and fuel taken in from the casing to generate a combustion gas;   a turbine driven by the combustion gas; and   an air introduction passage defined by a partition plate configured to divide the space in the casing in the circumferential direction of the rotor and an inner circumferential surface of the casing and configured to introduce the compressed air in the casing into the combustor.   
     
     
         2 . The gas turbine according to  claim 1 , wherein the partition plate is provided in the middle of each of the plurality of combustors. 
     
     
         3 . The gas turbine according to  claim 1 , wherein a baffle plate configured to bypass the compressed air is provided in the air introduction passage. 
     
     
         4 . The gas turbine according to  claim 2 , wherein a communication hole allowing communication between air introduction passages adjacent to each other in the circumferential direction is provided in the partition plate. 
     
     
         5 . The gas turbine according to  claim 2 , wherein a compressor outlet port flow channel is connected to the casing on an inner side in the radial direction of the rotor, and
 the partition plate extends to the compressor outlet port flow channel in the radial direction of the rotor, and divide the compressor outlet port flow channel into a plurality of sections in the circumferential direction of the rotor.   
     
     
         6 . A gas turbine comprising:
 a rotor that is rotatable about an axis;   a casing configured to cover the rotor in a circumferential direction and having an annular space therein;   a compressor configured to generate a high pressure of compressed air obtained by compressing external air and send the compressed air into the casing;   a plurality of combustors disposed in the casing at equal intervals in the circumferential direction of the rotor and configured to combust the compressed air and fuel taken in from the casing to generate a combustion gas;   a turbine driven by the combustion gas; and   an annular air introduction passage defined by a first cylinder section that surrounds the combustor and a second cylinder section that surrounds the first cylinder section and configured to introduce the compressed air in the casing into the combustor.   
     
     
         7 . A gas turbine comprising:
 a rotor that is rotatable about an axis;   a casing configured to cover the rotor in a circumferential direction and having an annular space therein;   a compressor configured to generate a high pressure of compressed air obtained by compressing external air and send the compressed air into the casing;   a plurality of combustors disposed in the casing at equal intervals in the circumferential direction of the rotor and configured to combust the compressed air and fuel taken in from the casing to generate a combustion gas;   a turbine driven by the combustion gas; and   an air introduction passage configured to introduce the compressed air in the casing into the combustor,   wherein the air introduction passage is defined by   a first wall section having an L-shaped cross section configured of a first plate section extending from an outer circumferential surface of the combustor and a second plate section extending from the first plate section toward a downstream side of the rotor in an axial direction, and   a second wall section having a U-shaped cross section configured of a third plate section extending from an inner circumferential surface of the casing toward the downstream side of the rotor in the axial direction, a fourth plate section extending from the third plate section toward the outer circumferential surface of the combustor and a fifth plate section extending from the fourth plate section toward the upstream side of the rotor in the axial direction, and   the second plate section of the first wall section is disposed between the third plate section and the fifth plate section of the second wall section.   
     
     
         8 . A gas turbine comprising:
 a rotor that is rotatable about an axis;   a casing configured to cover the rotor in a circumferential direction and having an annular space therein;   a compressor configured to generate a high pressure of compressed air obtained by compressing external air and send the compressed air into the casing;   a plurality of combustors disposed in the casing at equal intervals in the circumferential direction of the rotor and configured to combust the compressed air and fuel taken in from the casing to generate a combustion gas;   a turbine driven by the combustion gas; and   an air introduction passage defined by a plurality of guide pipes having a first opening section connected to an inlet port of the combustor and a second opening section that opens in the space in the casing on the downstream side in an axial direction of the rotor.   
     
     
         9 . The gas turbine according to  claim 1 , wherein the combustor includes:
 a combustor basket into which the compressed air is supplied from the casing through the air introduction passage;   a plurality of burners each of which extends in an axial direction of the combustor, is provided at intervals along an inner circumference of the combustor basket and has a nozzle configured to inject the fuel from a tip and a nozzle tube that concentrically surrounds the nozzle; and   a burner partition plate extending between the adjacent burners in the axial direction of the combustor and configured to divide an outlet port space of the air introduction passage in the combustor basket into independent sections for each of the burners.   
     
     
         10 . The gas turbine according to  claim 9 , wherein a burner communication hole in communication with the adjacent sections is provided in the burner partition plate. 
     
     
         11 . The gas turbine according to  claim 1 , wherein the combustor includes:
 a combustor basket into which the compressed air is supplied from the casing through the air introduction passage;   a plurality of burners each of which extends in an axial direction of the combustor, is provided at an interval along an inner circumference of the combustor basket and has a nozzle configured to inject the fuel from a tip and a nozzle tube that concentrically surrounds the nozzle; and   a fuel supply pipeline connected to each of the burners and configured to distribute and supply the fuel to the burners.   
     
     
         12 . The gas turbine according to  claim 1 , wherein the combustor includes:
 a combustor basket into which the compressed air is supplied from the casing through the air introduction passage;   a plurality of burners each of which extends in an axial direction of the combustor, is provided at an interval along an inner circumference of the combustor basket and has a nozzle configured to inject the fuel from a tip and a nozzle tube that concentrically surround the nozzles; and   a fuel circulation pipeline in communication with the burners and into which the fuel supplied to each of the burners between the burners flows.