Flow Integrating Section for a Gas Turbine Engine in Which Turbine Blades are Cooled by Full Compressor Flow

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Description

Routing of full compressor flow through hollow turbine blades achieves unusually effective blade cooling and allows a significant increase in turbine inlet gas temperature and, hence, engine efficiency. The invention, ''flow integrating section'' alleviates the turbine dissipation of kinetic energy of air jets leaving the hollow blades as they enter the compressor diffuser.

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Medium: P; Size: vp.

Creation Information

Steward, W. Gene November 14, 1999.

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Description

Routing of full compressor flow through hollow turbine blades achieves unusually effective blade cooling and allows a significant increase in turbine inlet gas temperature and, hence, engine efficiency. The invention, ''flow integrating section'' alleviates the turbine dissipation of kinetic energy of air jets leaving the hollow blades as they enter the compressor diffuser.

Physical Description

Medium: P; Size: vp.

Notes

OSTI as DE00764563

Source

  • Other Information: PBD: 14 Nov 1999

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  • Report No.: Final
  • Grant Number: FG01-97EE15668
  • DOI: 10.2172/764563 | External Link
  • Office of Scientific & Technical Information Report Number: 764563
  • Archival Resource Key: ark:/67531/metadc724103

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Office of Scientific & Technical Information Technical Reports

Reports, articles and other documents harvested from the Office of Scientific and Technical Information.

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Creation Date

  • November 14, 1999

Added to The UNT Digital Library

  • Sept. 29, 2015, 5:31 a.m.

Description Last Updated

  • March 24, 2016, 9:43 p.m.

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Steward, W. Gene. Flow Integrating Section for a Gas Turbine Engine in Which Turbine Blades are Cooled by Full Compressor Flow, report, November 14, 1999; United States. (digital.library.unt.edu/ark:/67531/metadc724103/: accessed October 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.