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Title: Method and apparatus for preventing overspeed in a gas turbine

Abstract

A method and apparatus for preventing overspeed in a gas turbine in response to the rapid loss of applied load is disclosed. The method involves diverting gas from the inlet of the turbine, bypassing the same around the turbine and thereafter injecting the diverted gas at the turbine exit in a direction toward or opposing the flow of gas through the turbine. The injected gas is mixed with the gas exiting the turbine to thereby minimize the thermal shock upon equipment downstream of the turbine exit.

Inventors:
 [1]
  1. (San Diego, CA)
Publication Date:
Research Org.:
General Atomic Co., San Diego, Calif. (USA)
OSTI Identifier:
862729
Patent Number(s):
US 3998047
Assignee:
United States of America as represented by United States Energy (Washington, DC) OSTI
DOE Contract Number:  
E(04-3)-167
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
method; apparatus; preventing; overspeed; gas; turbine; response; rapid; loss; applied; load; disclosed; involves; diverting; inlet; bypassing; thereafter; injecting; diverted; exit; direction; opposing; flow; injected; mixed; exiting; minimize; thermal; shock; equipment; downstream; thermal shock; method involves; gas turbine; preventing overspeed; gas exit; injected gas; applied load; method involve; gas exiting; /60/

Citation Formats

Walker, William E. Method and apparatus for preventing overspeed in a gas turbine. United States: N. p., 1976. Web.
Walker, William E. Method and apparatus for preventing overspeed in a gas turbine. United States.
Walker, William E. Thu . "Method and apparatus for preventing overspeed in a gas turbine". United States. doi:. https://www.osti.gov/servlets/purl/862729.
@article{osti_862729,
title = {Method and apparatus for preventing overspeed in a gas turbine},
author = {Walker, William E.},
abstractNote = {A method and apparatus for preventing overspeed in a gas turbine in response to the rapid loss of applied load is disclosed. The method involves diverting gas from the inlet of the turbine, bypassing the same around the turbine and thereafter injecting the diverted gas at the turbine exit in a direction toward or opposing the flow of gas through the turbine. The injected gas is mixed with the gas exiting the turbine to thereby minimize the thermal shock upon equipment downstream of the turbine exit.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Thu Jan 01 00:00:00 EST 1976},
month = {Thu Jan 01 00:00:00 EST 1976}
}

Patent:

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