Power generation system exhaust cooling

Patent metadata

Field	Value
Publication number	US-2016376955-A1
Application number	US-201514753077-A
Country	US
Kind code	A1
Filing date	Jun 29, 2015
Priority date	Jun 29, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

An airflow system for a gas turbine system according to an embodiment includes: a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

First claim

What is claimed is:

1 . An airflow control system for a gas turbine system, comprising:
a compressor component of a gas turbine system; an airflow generation system for attachment to a rotatable shaft of the gas turbine system, the airflow generation system and the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; and an air extraction system for extracting at least a portion of the excess flow of air generated by the airflow generation system and the compressor component to provide bypass air, and for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream.

2 . The airflow control system of claim 1 , wherein the excess flow of air generated by the airflow generation system and the compressor component is about 10% to about 40% greater than a flow rate capacity of at least one of a combustor component and a turbine component of the gas turbine system.

3 . The airflow control system of claim 1 , wherein the compressor component of the gas turbine system includes at least one oversized compressor stage.

4 . The airflow control system of claim 1 , wherein the airflow generation system comprises a fan.

5 . The airflow control system of claim 1 , wherein the air extraction system comprises a bypass duct for diverting the bypass air around the gas turbine system into the mixing area to reduce the temperature of the exhaust gas stream.

6 . The airflow control system of claim 1 , wherein the air extraction system comprises an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream.

7 . The airflow control system of claim 6 , further comprising a flow directing system for directing the bypass air toward and into the exhaust gas stream in the mixing area, wherein the flow directing system comprises an inwardly curved end portion of the enclosure and/or at least one outlet guide vane.

8 . The airflow control system of claim 1 , wherein the air extraction system is configured to divert a portion of the excess flow of air into the compressor component to supercharge the gas turbine system.

9 . The airflow control system of claim 1 , further comprising a selective catalytic reduction (SCR) system for processing the reduced temperature exhaust gas stream.

10 . A turbomachine system, comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, wherein the compressor component of the gas turbine system includes at least one oversized compressor stage; a shaft driven by the turbine component; a fan coupled to the shaft upstream of the gas turbine system, the fan and the at least one oversized compressor stage of the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the fan and the at least one oversized compressor stage of the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

11 . The turbomachine system of claim 10 , wherein the excess flow of air generated by the fan and the at least one oversized compressor stage of the compressor component is about 10% to about 40% greater than a flow rate capacity of at least one of the combustor component and the turbine component of the gas turbine system.

12 . The turbomachine system of claim 10 , wherein the air extraction system comprises a bypass duct for diverting the bypass air around the gas turbine system into the mixing area to reduce the temperature of the exhaust gas stream.

13 . The turbomachine system of claim 10 , wherein the air extraction system comprises an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream.

14 . The turbomachine system of claim 13 , further comprising a flow directing system for directing the bypass air toward and into the exhaust gas stream in the mixing area, wherein the flow directing system comprises an inwardly curved end portion of the enclosure and/or at least one outlet guide vane.

15 . The turbomachine system of claim 10 , wherein the air extraction system is configured to divert a portion of the excess flow of air into the compressor component to
supercharge the gas turbine system.

16 . The turbomachine system of claim 10 , wherein the exhaust processing system comprises a selective catalytic reduction (SCR) system.

17 . A power generation system, comprising:
a gas turbine system including a compressor component, a combustor component, and a turbine component, wherein the compressor component of the gas turbine system includes at least one oversized compressor stage; a shaft driven by the turbine component; an electrical generator coupled to the shaft for generating electricity; a fan coupled to the shaft upstream of the gas turbine system, the fan and the at least one oversized compressor stage of the compressor component drawing in an excess flow of air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; an air extraction system for: extracting at least a portion of the excess flow of air generated by the fan and the at least one oversized compressor stage of the compressor component to provide bypass air; and diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

18 . The power generation system of claim 17 , wherein the excess flow of air generated by the fan and the at least one oversized compressor stage of the compressor component is about 10% to about 40% greater than a flow rate capacity of at least one of the combustor component and the turbine component of the gas turbine system.

19 . The power generation system of claim 17 , wherein the air extraction system comprises:
a bypass duct for diverting the bypass air around the gas turbine system into the mixing area to reduce the temperature of the exhaust gas stream; or an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage and around the gas turbine system into the mixing area to reduce a temperature of the exhaust gas stream.

20 . The power generation system of claim 17 , wherein the exhaust processing system comprises a selective catalytic reduction (SCR) system.

Assignees

• Gen Electric

Inventors

• Reed Robert Joseph
• Davis Jr Lewis Berkley
• Kulkarni Parag Prakash

Classifications

• F05D2260/606

  Bypassing the fluid · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/305 Primary

  with fluid, e.g. liquid injection · CPC title

• F01N2610/14

  Arrangements for the supply of substances, e.g. conduits · CPC title