Impingement panel for a turbomachine
Abstract
An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.
- Inventors:
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1893082
- Patent Number(s):
- 11371702
- Application Number:
- 17/007,068
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- DOE Contract Number:
- FE0023965
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 08/31/2020
- Country of Publication:
- United States
- Language:
- English
Citation Formats
Berry, Jonathan Dwight, and Hughes, Michael John. Impingement panel for a turbomachine. United States: N. p., 2022.
Web.
Berry, Jonathan Dwight, & Hughes, Michael John. Impingement panel for a turbomachine. United States.
Berry, Jonathan Dwight, and Hughes, Michael John. Tue .
"Impingement panel for a turbomachine". United States. https://www.osti.gov/servlets/purl/1893082.
@article{osti_1893082,
title = {Impingement panel for a turbomachine},
author = {Berry, Jonathan Dwight and Hughes, Michael John},
abstractNote = {An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2022},
month = {6}
}
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