公开(公告)号：US10920599B2

公开(公告)日：2021-02-16

申请号：US16263063

申请日：2019-01-31

Applicant: United Technologies Corporation

Inventor： Abhir A. Adhate ,  Frank M. Prior ,  Kalman V. Wagner

IPC: F01D9/04

Abstract: A vane for a gas turbine engine according to an example of the present disclosure includes, among other things, first and second endwalls each having a radially facing surface that bounds a gas path, an airfoil section extending in a radial direction between the first and second endwalls, extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and extending in a circumferential direction between pressure and suction sides. The radially facing surface of each of the first and second endwalls is axially sloped such that the gas path converges in the axial direction between the airfoil leading and trailing edges. The first endwall has an axisymmetric contour at least partially swept in the circumferential direction from each of the pressure and suction sides.

公开(公告)号：US20200248572A1

公开(公告)日：2020-08-06

申请号：US16263063

申请日：2019-01-31

Applicant: United Technologies Corporation

Inventor： Abhir A. Adhate ,  Frank M. Prior ,  Kalman V. Wagner

IPC: F01D9/04

Abstract: A vane for a gas turbine engine according to an example of the present disclosure includes, among other things, first and second endwalls each having a radially facing surface that bounds a gas path, an airfoil section extending in a radial direction between the first and second endwalls, extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and extending in a circumferential direction between pressure and suction sides. The radially facing surface of each of the first and second endwalls is axially sloped such that the gas path converges in the axial direction between the airfoil leading and trailing edges. The first endwall has an axisymmetric contour at least partially swept in the circumferential direction from each of the pressure and suction sides.

公开(公告)号：US20180080472A1

公开(公告)日：2018-03-22

申请号：US15272310

申请日：2016-09-21

Applicant: United Technologies Corporation

Inventor： Robert W. Fessenden ,  Abhir A. Adhate ,  Yuan Dong ,  Sean Nolan ,  Li Xing Pan

IPC: F04D29/52 ,  F04D29/32

CPC classification number: F04D29/526 ,  F01D5/12 ,  F01D11/14 ,  F01D25/24 ,  F04D29/164 ,  F04D29/324 ,  F05D2220/32 ,  F05D2230/50

Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.