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Title: Turbomachine rotor with improved cooling

Abstract

A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn. 5 figs.

Inventors:
; ; ;
Publication Date:
Research Org.:
Westinghouse Electric Corporation
Sponsoring Org.:
USDOE, Washington, DC (United States)
OSTI Identifier:
644382
Patent Number(s):
US 5,755,556/A/
Application Number:
PAN: 8-649,507
Assignee:
Westinghouse Electric Corp., Pittsburgh, PA (United States) PTO; SCA: 330103; PA: EDB-98:093788; SN: 98001993213
DOE Contract Number:  
AC21-93MC30247
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 26 May 1998
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; ROTORS; COOLING SYSTEMS; HEAT RECOVERY

Citation Formats

Hultgren, K.G., McLaurin, L.D., Bertsch, O.L., and Lowe, P.E.. Turbomachine rotor with improved cooling. United States: N. p., 1998. Web.
Hultgren, K.G., McLaurin, L.D., Bertsch, O.L., & Lowe, P.E.. Turbomachine rotor with improved cooling. United States.
Hultgren, K.G., McLaurin, L.D., Bertsch, O.L., and Lowe, P.E.. Tue . "Turbomachine rotor with improved cooling". United States.
@article{osti_644382,
title = {Turbomachine rotor with improved cooling},
author = {Hultgren, K.G. and McLaurin, L.D. and Bertsch, O.L. and Lowe, P.E.},
abstractNote = {A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn. 5 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue May 26 00:00:00 EDT 1998},
month = {Tue May 26 00:00:00 EDT 1998}
}