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

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