Title:
COOLED COMBUSTOR FOR GAS TURBINE ENGINE
Document Type and Number:
Japanese Patent JP2017089638
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine engine, and a method of cooling a combustor of a gas turbine engine.SOLUTION: A combustor (30) for a gas turbine engine (10) comprises a combustion liner (78) to define a combustion chamber (80) for burning fuel to drive a turbine (34). The combustion liner (78) comprises a plurality of nugget holes (84) for providing cooling fluid to create a cooling film over a surface of the combustion liner (78) adjacent to the combustion chamber (80). The nugget holes (84) can be circumferentially angled relative to an engine centerline (12) to provide the flow of cooling fluid in an angled manner to align with a local streamline flow (170) of fluid from the combustor (30).SELECTED DRAWING: Figure 1
Inventors:
HOJJAT NASR
ZHANG JUNTAO
JESSICA SCHLADT
CRAIG ALAN GONYOU
ZHANG JUNTAO
JESSICA SCHLADT
CRAIG ALAN GONYOU
Application Number:
JP2016214743A
Publication Date:
May 25, 2017
Filing Date:
November 02, 2016
Export Citation:
Assignee:
GENERAL ELECTRIC CO GE
International Classes:
F02C7/18; F23R3/02; F23R3/08; F23R3/12; F23R3/50
Domestic Patent References:
| JP2003114023A | 2003-04-18 | |||
| JP2003065538A | 2003-03-05 |
Attorney, Agent or Firm:
Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka
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