公开(公告)号：US10221859B2

公开(公告)日：2019-03-05

申请号：US15018126

申请日：2016-02-08

Applicant: General Electric Company

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

IPC: F04D29/32

Abstract: 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

Applicant: General Electric Company

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

IPC: F04D29/32

CPC classification number: F04D29/324 ,  F01D5/141 ,  F05D2240/303 ,  F05D2240/304 ,  Y02T50/673

Abstract: 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.