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Title: Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

Abstract

A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Inventors:
; ; ;
Issue Date:
Research Org.:
Siemens Aktiengesellschaft, Munchen, DE (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1182596
Patent Number(s):
9,039,371
Application Number:
14/068,070
Assignee:
Siemens Aktiengesellschaft (Munchen, DE) DOESC
DOE Contract Number:  
SC0001359
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 17 WIND ENERGY

Citation Formats

Lee, Ching-Pang, Heneveld, Benjamin E., Brown, Glenn E., and Klinger, Jill. Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements. United States: N. p., 2015. Web.
Lee, Ching-Pang, Heneveld, Benjamin E., Brown, Glenn E., & Klinger, Jill. Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements. United States.
Lee, Ching-Pang, Heneveld, Benjamin E., Brown, Glenn E., and Klinger, Jill. Tue . "Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements". United States. https://www.osti.gov/servlets/purl/1182596.
@article{osti_1182596,
title = {Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements},
author = {Lee, Ching-Pang and Heneveld, Benjamin E. and Brown, Glenn E. and Klinger, Jill},
abstractNote = {A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {5}
}

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Works referenced in this record:

Designing a Turbine Blade Cooling System Using a Generalised Regression Genetic Algorithm
journal, January 2003