Invention Grant
- Patent Title: Tunable transition duct side seals in a gas turbine engine
- Patent Title (中): 燃气涡轮发动机中可调节的过渡管道侧密封
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Application No.: US12901084Application Date: 2010-10-08
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Publication No.: US09121279B2Publication Date: 2015-09-01
- Inventor: Sherman Craig Creighton , Charles Ellis , David John Henriquez , Peter Stuttaford
- Applicant: Sherman Craig Creighton , Charles Ellis , David John Henriquez , Peter Stuttaford
- Applicant Address: CH Baden
- Assignee: Alstom Technology Ltd
- Current Assignee: Alstom Technology Ltd
- Current Assignee Address: CH Baden
- Agency: Shook, Hardy & Bacon L.L.P.
- Main IPC: F23R3/02
- IPC: F23R3/02 ; F23R3/26 ; F01D9/02 ; F01D11/00

Abstract:
A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.
Public/Granted literature
- US20120085099A1 TUNABLE SEAL IN A GAS TURBINE ENGINE Public/Granted day:2012-04-12
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