Arrangement for a gas turbine combustion engine
Abstract
An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).
- Inventors:
- Issue Date:
- Research Org.:
- SIEMENS ENERGY, INC., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1494574
- Patent Number(s):
- 10132175
- Application Number:
- 15/509,987
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2014 Oct 07
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
Little, David A. Arrangement for a gas turbine combustion engine. United States: N. p., 2018.
Web.
Little, David A. Arrangement for a gas turbine combustion engine. United States.
Little, David A. Tue .
"Arrangement for a gas turbine combustion engine". United States. https://www.osti.gov/servlets/purl/1494574.
@article{osti_1494574,
title = {Arrangement for a gas turbine combustion engine},
author = {Little, David A.},
abstractNote = {An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {11}
}
Works referenced in this record:
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patent, September 2007
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- US Patent Document 7,270,175
Cooling structure for gas turbine transition duct
patent, September 2011
- Charron, Richard C.; Snyder, Gary; Landis, Kenneth K.
- US Patent Document 8,015,817
Transition with a linear flow path for use in a gas turbine engine
patent, February 2012
- Charron, Richard C.; Montgomery, Matthew; Snyder, Gary
- US Patent Document 8,113,003
Industrial stator vane with sequential impingement cooling inserts
patent, August 2013
- Jones, Russell B.; Fedock, John A.; Goebel, Gloria E.
- US Patent Document 8,500,405