Gas Turbine Engine With Vane Having A Cooling Inlet

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine [10], such as a multi-stage compressor [24, 26] of a gas turbine engine [10], by reducing an operating air temperature in a space [130] between a seal [128] and a blade post [112] of adjacent stages [52, 54] by routing cooling air through an inlet [140] in the vane , passing the routed cooling air through the vane [62], and emitting the routed cooling air into the space [130].

Patent Information

Application #

Filing Date

14 November 2016

Publication Number

20/2017

Publication Type

INA

Invention Field

MECHANICAL ENGINEERING

Status

Email

bpo.mail@ge.com

Parent Application

Applicants

GENERAL ELECTRIC COMPANY

1 River Road, Schenectady, New York 12345, United States of America

Inventors

1. SUBRAMANIAN, Sesha

John F. Welch Technology Center, 122, EPIP Phase-2, Hoodi, Village, Whitefield, Bangalore 560066, India

2. SHELTON, Monty Lee

1 Neumann Way, CPT4, MD S136, Cincinnati, OH 45215, USA

3. PROCTOR, Robert

1 Neumann Way, MDJ161, Cincinnati, OH 45215, USA

4. THOPPIL, Mohamed Musthafa

John F. Welch Technology Center, 122, EPIP Phase-2, Hoodi Village, Whitefield, Bangalore 560066, India

5. GURRAM, Venkateswararao

John F. Welch Technology Center, 122, EPIP Phase-2, Hoodi Village, Whitefield, Bangalore 560066, India

6. JOINER, Josiah Warren

9025 Centre Pointe Drive, West Chester, OH 45069, USA

7. SAK, Wojciech

9100 Centre Pointe Drive, West Chester, OH 45069-4846, USA

Specification

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