Power generation system exhaust cooling

Patent metadata

Field	Value
Publication number	US-2016376908-A1
Application number	US-201514753088-A
Country	US
Kind code	A1
Filing date	Jun 29, 2015
Priority date	Jun 29, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A power generation system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; a shaft driven by the turbine component; an airflow generation system coupled to the shaft upstream 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 an 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; an exhaust processing system for processing the reduced temperature exhaust gas stream; and an air diversion system for diverting a portion of the bypass air to the exhaust processing system.

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; 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; and an air diversion system for diverting a portion of the bypass air to an exhaust processing system.

2 . The turbomachine 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 turbomachine system of claim 1 , wherein the compressor component of the gas turbine system includes at least one oversized compressor stage, and wherein the airflow generation system comprises a fan.

4 . The turbomachine system of claim 1 , wherein the exhaust processing system comprises a selective catalytic reduction (SCR) system for processing the reduced temperature exhaust gas stream.

5 . The turbomachine system of claim 4 , wherein the exhaust processing system further comprises a reductant evaporator system for evaporating a supply of a reductant and a reductant injection system for injecting the evaporated reductant into the reduced temperature exhaust gas stream upstream of the SCR system.

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

7 . The turbomachine system of claim 6 , wherein the air diversion system further comprises an air conduit and a flow a control component for selectively controlling the flow of air through the air conduit, the air conduit fluidly coupling the bypass duct and the reductant evaporator system, wherein the diverted portion of the bypass air is provided to the reductant evaporator system through the air conduit to evaporate the reductant.

8 . The turbomachine system of claim 5 , wherein the air extraction system further comprises an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage into the mixing area to reduce a temperature of the exhaust gas stream.

9 . The turbomachine system of claim 8 , wherein the air diversion system further comprises an air conduit and a flow a control component for selectively controlling the flow of air through the air conduit, the air conduit fluidly coupling the enclosure and the reductant evaporator system, wherein the diverted portion of the bypass air is provided to the reductant evaporator system through the air conduit to evaporate the reductant.

10 . The turbomachine system of claim 5 , wherein the reductant includes ammonia.

11 . 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 an 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 for diverting the bypass air into the mixing area to reduce a temperature of the exhaust gas stream; an exhaust processing system for processing the reduced temperature exhaust gas stream, wherein the exhaust processing system comprises a selective catalytic reduction (SCR) system; and an air diversion system for diverting a portion of the bypass air to the exhaust processing system.

12 . The power generation system of claim 11 , wherein the excess flow of air generated by the airflow generation system and the at least one oversized compressor stage of the compressor component is about 10 percent to about 40 percent more air than is used by the gas turbine system.

13 . The power generation system of claim 11 , wherein the exhaust processing system further comprises a reductant evaporator system for evaporating a supply of a reductant and a reductant injection system for injecting the evaporated reductant into the reduced temperature exhaust gas stream upstream of the SCR system.

14 . The power generation system of claim 13 , wherein the air extraction system further 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.

15 . The power generation system of claim 14 , wherein the air diversion system further comprises an air conduit and a flow a control component for selectively controlling the flow of air through the air conduit, the air conduit fluidly coupling the bypass duct and the reductant evaporator system, wherein the diverted portion of the bypass air is provided to the reductant evaporator system through the air conduit to evaporate the reductant.

16 . The power generation system of claim 13 , wherein the air extraction system further comprises an enclosure surrounding the gas turbine system and forming an air passage, the bypass air flowing through the air passage into the mixing area to reduce the temperature of the exhaust gas stream.

17 . The power generation system of claim 16 , wherein the air diversion system further comprises an air conduit and a flow a control component for selectively controlling the flow of air through the air conduit, the air conduit fluidly coupling the enclosure and the reductant evaporator system, wherein the diverted portion of the bypass air is provided to the reductant evaporator system through the air conduit to evaporate the reductant.

18 . The power generation system of claim 13 , wherein the reductant includes ammonia.

19 . 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 an 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 for diverting the bypass air

Assignees

• Gen Electric

Inventors

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

Classifications

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01N3/2066

  Selective catalytic reduction [SCR] · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title