Transition nozzle combustion system
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.
- Issue Date:
- OSTI Identifier:
- 1333736
- Assignee:
- GENERAL ELECTRIC COMPANY (Schenectady, NY) NETL
- Patent Number(s):
- 9,506,359
- Application Number:
- 13/437,953
- Contract Number:
- FC26-05NT42643
- Resource Relation:
- Patent File Date: 2012 Apr 03
- Research Org:
- GENERAL ELECTRIC COMPANY, Schenectady, NY (United States)
- Sponsoring Org:
- USDOE
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS
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Other works cited in this record:
Gas Turbine Enginepatent, March 1966
- Hill, Henry
- US Patent Document 3,238,718
Combination transition piece floating cloth seal and stage 1 turbine nozzle flexible sealing element
patent, April 2003
- Cromer, Robert Harold
- US Patent Document 6,547,257
Dynamically uncoupled can combustor
patent, January 2005
- Han, Fei; Dinc, Osman; Mohammed-Fakir, Abdul-Azeez
- US Patent Document 6,840,048
Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010
- Bancalari, Eduardo; Wilson, Jody; Little, David A.
- US Patent Document 7,721,547
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