skip to main content
DOE Patents title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: End wall configuration for gas turbine engine

Abstract

A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).

Inventors:
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1576303
Patent Number(s):
10415392
Application Number:
15/307,087
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2014 Jun 18
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Lohaus, Andrew S. End wall configuration for gas turbine engine. United States: N. p., 2019. Web.
Lohaus, Andrew S. End wall configuration for gas turbine engine. United States.
Lohaus, Andrew S. Tue . "End wall configuration for gas turbine engine". United States. https://www.osti.gov/servlets/purl/1576303.
@article{osti_1576303,
title = {End wall configuration for gas turbine engine},
author = {Lohaus, Andrew S.},
abstractNote = {A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2019},
month = {9}
}

Patent:

Save / Share: