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Title:
METHOD AND SYSTEM FOR A GAS TURBINE ENGINE WITH A STAGE TWO BLADE COOLING DELIVERY CIRCUIT
Document Type and Number:
WIPO Patent Application WO/2018/140130
Kind Code:
A3
Abstract:
The turbine includes a first turbine rotor disc, a second turbine rotor disc, a first source of cooling fluid, and a first cooling fluid conduit. The first turbine rotor disc has a first outer circumference and a first plurality of blades spaced along the first outer circumference. The second turbine rotor disc has a second outer circumference and a second plurality of blades spaced along the second outer circumference. The first cooling fluid conduit is configured to channel a first flow of cooling fluid from the first source of cooling fluid through the first turbine rotor disc to a blade of the second plurality of blades.

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Inventors:
JOHNSON BRIAN (US)
WASLO DANIEL (US)
Application Number:
PCT/US2017/063315
Publication Date:
November 01, 2018
Filing Date:
November 27, 2017
Export Citation:
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Assignee:
GEN ELECTRIC (US)
International Classes:
F02C9/18; F01D25/12; F02C6/04; F02C7/143
Foreign References:
US20100290922A12010-11-18
US5795130A1998-08-18
US20160003166A12016-01-07
US20140030073A12014-01-30
US20150354456A12015-12-10
Attorney, Agent or Firm:
KACHUR, Pamela A. et al. (US)
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