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Title: Transition nozzle combustion system

Patent ·
OSTI ID:1333736
; ;

The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.

Research Organization:
General Electric Co., Schenectady, NY (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
GENERAL ELECTRIC COMPANY (Schenectady, NY)
Patent Number(s):
9,506,359
Application Number:
13/437,953
OSTI ID:
1333736
Resource Relation:
Patent File Date: 2012 Apr 03
Country of Publication:
United States
Language:
English

References (30)

Game Apparatus patent December 2022
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Combustor patent April 2008
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Combustion transition duct providing stage 1 tangential turning for turbine engines patent May 2010
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Multi-tube, can-annular pulse detonation combustor based engine with tangentially and longitudinally angled pulse detonation combustors patent-application October 2009
Transition with a linear flow path for use in a gas turbine engine patent-application February 2010
Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method patent-application May 2010
Cooling arrangement for a turbine component patent-application February 2012
Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine patent-application May 2012

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