公开(公告)号：US20180313364A1

公开(公告)日：2018-11-01

申请号：US15499731

申请日：2017-04-27

申请人： General Electric Company

发明人： Curtis William Moeckel ,  Matthew Ford Adam ,  Rudolf Konrad Selmeier ,  Michael Anthony Thomas ,  Steven Mitchell Taylor ,  Anton Streit

IPC分类号： F04D29/54 ,  F04D27/00 ,  F02C3/04

摘要： A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row including a plurality of stator vanes disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, the bleed slot having an inlet and an outlet and extending along a slot axis, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the inboard and outboard walls diverging from each other in a downstream direction relative to the bleed slot; and a plurality of turning vanes disposed in the slot, the turning vanes configured to reduce a tangential velocity of airflow through the bleed slot.

公开(公告)号：US10221859B2

公开(公告)日：2019-03-05

申请号：US15018126

申请日：2016-02-08

申请人： General Electric Company

发明人： Curtis William Moeckel ,  Peter John Wood ,  Matthew Ford Adam ,  Eric Andrew Falk ,  Mark Joseph Stecher

IPC分类号： F04D29/32

摘要： An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.

公开(公告)号：US20170227016A1

公开(公告)日：2017-08-10

申请号：US15018126

申请日：2016-02-08

申请人： General Electric Company

发明人： Curtis William Moeckel ,  Peter John Wood ,  Matthew Ford Adam ,  Eric Andrew Falk ,  Mark Joseph Stecher

IPC分类号： F04D29/32

CPC分类号： F04D29/324 ,  F01D5/141 ,  F05D2240/303 ,  F05D2240/304 ,  Y02T50/673

摘要： An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.