公开(公告)号：US20180094544A1

公开(公告)日：2018-04-05

申请号：US15282547

申请日：2016-09-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Waslo

IPC: F01D25/28

Abstract: A core engine includes a first tierod and a compressor rotor assembly including a plurality of compressor rotor disks arranged in a face to face orientation and spaced along the first tierod. The core engine includes a second tierod and a turbine rotor assembly including a plurality of turbine rotor disks arranged in a face to face orientation and spaced along the second tierod. The compressor rotor assembly is aft of the turbine rotor assembly.

公开(公告)号：US20170328283A1

公开(公告)日：2017-11-16

申请号：US15150628

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Daniel Waslo ,  Michael Richardson-Bach

IPC: F02C9/18 ,  F01D5/02 ,  F01D25/12 ,  F02C3/04 ,  F01D9/04

CPC classification number: F02C9/18 ,  F01D5/02 ,  F01D5/04 ,  F01D9/04 ,  F01D25/12 ,  F02C3/04 ,  F02C3/05 ,  F02C3/08 ,  F02C6/08 ,  F05D2220/32 ,  F05D2240/127 ,  F05D2260/20 ,  F05D2260/209 ,  Y02T50/676

Abstract: The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.