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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}
}

Works referenced in this record:

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patent, May 2013


Endwall shape for use in turbomachinery
patent, December 2003


Crescentic ramp turbine stage
patent, May 2007


Funnel fillet turbine stage
patent, July 2007


Aerofoil members for a turbomachine
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Turbine nozzle having non-axisymmetric endwall contour (EWC)
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Airfoil array with an endwall depression and components of the array
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patent, May 2012


Endwall with leading-edge hump
patent, January 2012


Wall configuration of axial-flow machine, and gas turbine engine
patent, April 2010


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patent, June 2013


Methods and apparatus relating to improved turbine blade platform contours
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patent, May 2003


Fillet energized turbine stage
patent, May 2007


Scalloped surface turbine stage with trailing edge ridges
patent, June 2012


Airfoil array with an endwall protrusion and components of the array
patent, February 2011


Gas turbine engine with non-axisymmetric surface contoured vane platform
patent, January 2013