公开(公告)号：DE3045224A1

公开(公告)日：1981-06-19

申请号：DE3045224

申请日：1980-12-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT HOWARD ,  RYNASKI CHESTER HAROLD ,  FULTON GRAHAM BRYANT

IPC: F04D29/38 ,  F01D5/14 ,  F01D5/30 ,  F01D11/00 ,  F04D29/34

Abstract: The present invention provides improvements to fan rotor blades of turbofan gas turbine engines. Increased low cycle fatigue life is sought, and a specific object is to obtain a more nearly uniform chordwise distribution of maximum stress levels across the root sections of fan blades. In one effective embodiment incorporating concepts of the present invention the root section of a fan blade is contoured to an arcuate geometry which approximates the contour of the airfoil cross section at the inner wall of the working medium flowpath. Further contour specifications for reducing local stress levels are discussed.

公开(公告)号：GB2208898A

公开(公告)日：1989-04-19

申请号：GB8819735

申请日：1988-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT HOWARD ,  LYONS KENT A ,  GRIFFIN EVANS E

IPC: F01D5/22 ,  F04D21/00 ,  F04D29/32

Abstract: A compressor blade assembly for a compressor operating at transonic or supersonic blade speeds has a part span shroud. The shroud is twisted having a first angle in the direction of airflow on one side of the shock wave and a second angle in the direction of airflow on the other side of the shock wave.

公开(公告)号：NO156502C

公开(公告)日：1987-10-07

申请号：NO803544

申请日：1980-11-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT HOWARD ,  RYNASKI CHESTER HAROLD ,  FULTON GRAHAM BRYANT

IPC: F01D5/14 ,  F04D29/38 ,  F01D5/30 ,  F01D11/00 ,  F04D29/34

Abstract: The present invention provides improvements to fan rotor blades of turbofan gas turbine engines. Increased low cycle fatigue life is sought, and a specific object is to obtain a more nearly uniform chordwise distribution of maximum stress levels across the root sections of fan blades. In one effective embodiment incorporating concepts of the present invention the root section of a fan blade is contoured to an arcuate geometry which approximates the contour of the airfoil cross section at the inner wall of the working medium flowpath. Further contour specifications for reducing local stress levels are discussed.

公开(公告)号：GB2208898B

公开(公告)日：1992-02-19

申请号：GB8819735

申请日：1988-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT HOWARD ,  LYONS KENT A ,  GRIFFIN EVANS E

IPC: F01D5/22 ,  F04D21/00 ,  F04D29/32

Abstract: A compressor blade assembly for a compressor operating at transonic or supersonic blade speeds has a part span shroud. The shroud is twisted having a first angle in the direction of airflow on one side of the shock wave and a second angle in the direction of airflow on the other side of the shock wave.

公开(公告)号：NO803544A

公开(公告)日：1981-06-01

申请号：NO803544

申请日：1980-11-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT HOWARD ,  RYNASKI CHESTER HAROLD ,  FULTON GRAHAM BRYANT

IPC: F04D29/38 ,  F01D5/14 ,  F01D5/30 ,  F01D11/00 ,  F04D29/34 ,  F01D

CPC classification number: F01D5/3007 ,  F01D5/141 ,  F01D11/008 ,  Y02T50/673

公开(公告)号：NO803544L

公开(公告)日：1981-06-01

申请号：NO803544

申请日：1980-11-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT HOWARD ,  RYNASKI CHESTER HAROLD ,  FULTON GRAHAM BRYANT

IPC: F01D5/14 ,  F04D29/38 ,  F01D5/30 ,  F01D11/00 ,  F04D29/34 ,  F01D

Abstract: The present invention provides improvements to fan rotor blades of turbofan gas turbine engines. Increased low cycle fatigue life is sought, and a specific object is to obtain a more nearly uniform chordwise distribution of maximum stress levels across the root sections of fan blades. In one effective embodiment incorporating concepts of the present invention the root section of a fan blade is contoured to an arcuate geometry which approximates the contour of the airfoil cross section at the inner wall of the working medium flowpath. Further contour specifications for reducing local stress levels are discussed.