公开(公告)号：JPH116499A

公开(公告)日：1999-01-12

申请号：JP11173098

申请日：1998-04-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT H ,  SPAULDING REGINALD H ,  TODD EDWARD S

IPC: F02C7/04 ,  F01D5/14 ,  F01D21/04 ,  F04D29/08 ,  F04D29/38

Abstract: PROBLEM TO BE SOLVED: To provide a fan blade for axial flow gas turbine engine having durability. SOLUTION: A blade platform 46 is formed such that the breakage end part of a platform is held in a root part, and a blade part adjoining to the blade is broken. As a result of the so formed platform being used, the damage of a subsequent blade on a blade defective condition is reduced. In addition, by modifying detailed parts of various kinds of constitution, the damage of the blade when an impact is exerted on an adjoining fan blade is reduced.

公开(公告)号：FR2619868B1

公开(公告)日：1990-07-20

申请号：FR8811123

申请日：1988-08-23

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/22 ,  F04D21/00 ,  F04D29/32 ,  F04D29/38 ,  F02C7/00

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：DE69817065D1

公开(公告)日：2003-09-18

申请号：DE69817065

申请日：1998-04-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT H ,  SPAULDING REGINALD H ,  TODD EDWARD S ,  KASPROW ROBERT F ,  KLAPPROTH HERMAN C ,  WELCH DOUGLAS A ,  KURZ PHYLLIS L ,  CAFASSO JOSEPH J

IPC: F02C7/04 ,  F01D5/14 ,  F01D21/04 ,  F04D29/08 ,  F04D29/38

公开(公告)号：DE69817065T2

公开(公告)日：2004-04-08

申请号：DE69817065

申请日：1998-04-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT H ,  SPAULDING REGINALD H ,  TODD EDWARD S ,  KASPROW ROBERT F ,  KLAPPROTH HERMAN C ,  WELCH DOUGLAS A ,  KURZ PHYLLIS L ,  CAFASSO JOSEPH J

IPC: F02C7/04 ,  F01D5/14 ,  F01D21/04 ,  F04D29/08 ,  F04D29/38

公开(公告)号：FR2619868A1

公开(公告)日：1989-03-03

申请号：FR8811123

申请日：1988-08-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZIPPS ROBERT H ,  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.