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Title: Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine

Abstract

An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38). The converging-diverging exit slot (20) may be formed from a first converging section (84) having an inlet (86) with a larger cross-sectional area than an outlet (88) and is formed from a second diverging section (90) having an inlet (92) with a smaller cross-sectional area than an outlet (94).

Inventors:
; ; ;
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1473671
Patent Number(s):
10,060,270
Application Number:
15/552,882
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2015 Mar 17
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Lee, Ching-Pang, Myers, Caleb, Johnson, Erik, and Koester, Steven. Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine. United States: N. p., 2018. Web.
Lee, Ching-Pang, Myers, Caleb, Johnson, Erik, & Koester, Steven. Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine. United States.
Lee, Ching-Pang, Myers, Caleb, Johnson, Erik, and Koester, Steven. Tue . "Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine". United States. https://www.osti.gov/servlets/purl/1473671.
@article{osti_1473671,
title = {Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine},
author = {Lee, Ching-Pang and Myers, Caleb and Johnson, Erik and Koester, Steven},
abstractNote = {An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38). The converging-diverging exit slot (20) may be formed from a first converging section (84) having an inlet (86) with a larger cross-sectional area than an outlet (88) and is formed from a second diverging section (90) having an inlet (92) with a smaller cross-sectional area than an outlet (94).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {8}
}

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