Compressor bleed systems in turbomachines and methods of extracting compressor airflow

US10227930B2 · kind B2 · utility

Assignee

• General Electric Company · US

Inventors

• Swati Saxena · Schenectady, US
• Ajay Keshava Rao · Bengaluru, IN
• Rudolf Konrad Selmeier · Unterschleißheim, DE
• Grover Andrew Bennett · Schenectady, US
• Giridhar Jothiprasad · Clifton Park, US
• Corey Bourassa · Mechanicville, US
• Byron Andrew Pritchard, Jr. · Loveland, US

Key dates

• Filing date: Mar 28, 2016
• Grant date: Mar 12, 2019
• Expiry date: Mar 10, 2037

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/607
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.