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:
- Issue Date:
- Research Org.:
- Westinghouse Electric Corporation
- Sponsoring Org.:
- USDOE, Washington, DC (United States)
- OSTI Identifier:
- 644382
- Patent Number(s):
- 5755556
- Application Number:
- PAN: 8-649,507
- Assignee:
- Westinghouse Electric Corp., Pittsburgh, PA (United States)
- 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 = {1998},
month = {5}
}