Design and Production Methods of Gas Turbine

Patent metadata

Field	Value
Publication number	US-2016245305-A1
Application number	US-201615046881-A
Country	US
Kind code	A1
Filing date	Feb 18, 2016
Priority date	Feb 19, 2015
Publication date	Aug 25, 2016
Grant date	—

Abstract

An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200 . Under the condition that the annulus area of each stage of the compressor 38 becomes equal to the determined annulus area, an inner radius increment and an outer radius decrement of an initial stage 36 a are determined, the inner radius increment and the outer radius decrement of each of intermediate stages 36 b - 36 e are determined so that the inner radius increment is not more than the inner radius increment of the previous stage and the outer radius decrement is not less than the outer radius decrement of the previous stage, and the inner radius increment and the outer radius decrement of a final stage 36 f are determined so that the outer radius decrement is not less than the inner radius increment. The compressor 38 is designed by updating design data of components of the reference compressor 15 that deviated from the specifications due to the determination of the inner radius increment and the outer radius decrement so that the updated design data fulfill the specifications in each of the stages 36 a - 36 f.

First claim

What is claimed is:

1 . A gas turbine production method for producing a derivative gas turbine of a different cycle based on a reference gas turbine including a reference compressor, wherein:
letting a reference inner radius and a reference outer radius respectively represent an inner radius and an outer radius of an annular compressor channel of the reference compressor, an inner radius increment represent an increment in an inner radius of a compressor channel of the derivative gas turbine with respect to the reference inner radius, and an outer radius decrement represent a decrement in an outer radius of the compressor channel of the derivative gas turbine with respect to the reference outer radius, the gas turbine production method comprising the steps of: determining a compressor flow rate and a compression ratio required of a compressor of the derivative gas turbine; determining annulus areas required of the compressor of the derivative gas turbine based on the determined compressor flow rate and compression ratio; determining the inner radius increment and the outer radius decrement of an initial stage, determining the inner radius increment and the outer radius decrement of each of intermediate stages on the downstream side of the initial stage such that the inner radius increment is not more than the inner radius increment of the previous stage and the outer radius decrement is not less than the outer radius decrement of the previous stage, and determining the inner radius increment and the outer radius decrement of a final stage on the downstream side of the intermediate stages such that the outer radius decrement is not less than the inner radius increment under a condition that the annulus area of each stage of the compressor of the derivative gas turbine becomes equal to the determined annulus area; designing the compressor of the derivative gas turbine by updating design data of components of the reference compressor that deviated from specifications due to the determination of the inner radius increment and the outer radius decrement such that the updated design data fulfill the specifications in the initial stage, in each of the intermediate stages, and in the final stage; and producing the compressor of the derivative gas turbine based on the design and thereby producing the derivative gas turbine.

2 . The gas turbine production method according to claim 1 , wherein the inner radius increment is determined to be greater than the outer radius decrement in the initial stage.

3 . The gas turbine production method according to claim 1 , wherein decrements in the annulus areas of the reference compressor with respect to the determined annulus areas are made uniform.

4 . The gas turbine production method according to claim 1 , wherein in each stage on the downstream side of the initial stage, a decrement in the annulus area of the reference compressor with respect to the determined annulus area is made greater than the decrement in the previous stage.

5 . The gas turbine production method according to claim 1 , wherein:
the reference compressor includes outer radius constant stages in which the reference outer radius is constant from the initial stage toward the downstream side and an outer radius decreasing stage that connects to the outer radius constant stages and in which the reference outer radius decreases toward the downstream side, in the outer radius constant stages, the annulus area in each stage is made equal to the determined annulus area by uniformly decreasing the reference outer radii in the stages such that the reference outer radii become equal to the outer radius at a downstream end stage in the outer radius constant stages in a case where only the reference outer radii are decreased, while increasing the reference inner radii according to the decrement in the reference outer radii, and in the outer radius decreasing stage, the reference outer radius is decreased such that decrements in the annulus areas of the reference compressor with respect to the determined annulus areas become uniform.

6 . The gas turbine production method according to claim 1 , wherein at least one stage is added to the downstream side of the final stage.

7 . The gas turbine production method according to claim 1 , wherein inlet guide vanes each of which rotates around a shaft extending in a blade length direction as a rotary shaft are provided on the upstream side of the initial stage.

8 . A gas turbine design method for designing a derivative gas turbine of a different cycle based on a reference gas turbine including a reference compressor, wherein:
letting a reference inner radius and a reference outer radius respectively represent an inner radius and an outer radius of an annular compressor channel of the reference compressor, an inner radius increment represent an increment in an inner radius of a compressor channel of the derivative gas turbine with respect to the reference inner radius, and an outer radius decrement represent a decrement in an outer radius of the compressor channel of the derivative gas turbine with respect to the reference outer radius, the gas turbine design method comprising the steps of: determining a compressor flow rate and a compression ratio required of a compressor of the derivative gas turbine; determining annulus areas required of the compressor of the derivative gas turbine based on the determined compressor flow rate and compression ratio; determining the inner radius increment and the outer radius decrement of an initial stage, determining the inner radius increment and the outer radius decrement of each of intermediate stages on the downstream side of the initial stage such that the inner radius increment is not more than the inner radius increment of the previous stage and the outer radius decrement is not less than the outer radius decrement of the previous stage, and determining the inner radius increment and the outer radius decrement of a final stage on the downstream side of the intermediate stages such that the outer radius decrement is not less than the inner radius increment under a condition that the annulus area of each stage of the compressor of the derivative gas turbine becomes equal to the determined annulus area; and designing the compressor of the derivative gas turbine by updating design data of components of the reference compressor that deviated from specifications due to the determination of the inner radius increment and the outer radius decrement such that the updated design data fulfill the specifications in the initial stage, in each of the intermediate stages, and in the final stage, and thereby designing the derivative gas turbine.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Kimura Yasunori
• Shibata Takanori
• Takahashi Yasuo
• Tsukidate Hironori

Classifications

• F05D2230/50

  Building or constructing in particular ways · CPC title

• F04D19/00

  Axial-flow pumps (F04D21/00 takes precedence; {pump comprising axial flow and radial flow stages F04D17/025}) · CPC title

• F04D29/321

  for axial flow compressors · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F04D29/522 Primary

  especially adapted for elastic fluid pumps · CPC title