Process for retrofitting an industrial gas turbine engine for increased power and efficiency

a gas turbine engine and gas turbine technology, applied in the direction of engines, machines/engines, mechanical equipment, etc., can solve the problems of limited power and efficiency of single-shaft gas turbine engines, limited capability to be upgraded for either power or efficiency, and limited total flow, so as to increase the overall power rating and efficiency, the effect of increasing the firing temperatur

Inactive Publication Date: 2017-08-24
JONES RUSSELL B +3
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  • Application Information

AI Technical Summary

Benefits of technology

[0005]In the present invention, existing single shaft turbine engines are retrofitted with a low speed turbine coupled to a low speed compressor that is aerodynamically coupled in front of the existing compressor, now deemed the high compressor, where the existing tur...

Problems solved by technology

Single shaft gas turbine engines are limited in power and efficiency when pressure ratios and firing temperatures are raised to the point where the last turbine stage is loaded to where Mach numbers reach the maximum aero...

Method used

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  • Process for retrofitting an industrial gas turbine engine for increased power and efficiency
  • Process for retrofitting an industrial gas turbine engine for increased power and efficiency
  • Process for retrofitting an industrial gas turbine engine for increased power and efficiency

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Embodiment Construction

[0020]The present invention is a process for retrofitting an industrial gas turbine engine of a power plant for increased power and efficiency.

[0021]In the present invention, existing single shaft turbine engines 10 like that shown in FIG. 1 are retrofitted with a low speed turbine (LST) coupled to a low speed compressor (LSC) that is aerodynamically coupled in front of the existing compressor, now deemed the high pressure compressor (HPC), where the existing turbine (now deemed the high pressure turbine or HPT), is coupled aerodynamically to the low speed turbine (LST). The existing single shaft industrial gas turbine engine includes a compressor 11 driven by a turbine 13 with a combustor 12, and an electric generator 14 driven by the rotor on the cold side which is in front of the compressor 11. Bearings 15 support the rotor of the engine.

[0022]Further enhancements to the cooling systems enhance the ability to increase the firing temperature of the existing section of the gas turb...

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Abstract

A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application claims the benefit to U.S. Provisional Application 62 / 299,248 filed on Feb. 24, 2016 and entitled PROCESS FOR RETROFITTING AN INDUSTRIAL GAS TURBINE ENGINE FOR INCREASED POWER AND EFFICIENCY.GOVERNMENT LICENSE RIGHTS[0002]This invention was made with Government support under contract number DE-FE0023975 awarded by Department of Energy. The Government has certain rights in the invention.BACKGROUND OF THE INVENTIONField of the Invention[0003]The present invention relates generally to a power plant with an industrial gas turbine engine, and more specifically to a process for retrofitting an industrial gas turbine engine for increased power and efficiency.Description of the Related Art including information disclosed under 37 CFR 1.97 and 1.98[0004]Single shaft gas turbine engines are limited in power and efficiency when pressure ratios and firing temperatures are raised to the point where the last turbine stage is loaded to ...

Claims

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Application Information

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IPC IPC(8): F02C3/13F01D17/14F02C9/22F01D15/10F02C7/18F02C9/18
CPCF02C3/13F02C7/18F02C9/18F02C9/22F01D15/10F05D2230/80F05D2220/32F05D2240/35F05D2260/211F05D2260/202F01D17/14F02C3/00F02C6/00F05D2220/76
Inventor JONES, RUSSELL B.BROSTMEYER, JOSEPH D.CEJKA, JUSTIN T.RYZNIC, JOHN E.
Owner JONES RUSSELL B
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