公开(公告)号：CA1283366C

公开(公告)日：1991-04-23

申请号：CA550249

申请日：1987-10-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WEINGOLD HARRIS D ,  HARVEY WALTER B

IPC: F04D29/38 ,  B64C11/18 ,  F01D5/14 ,  F04D21/00

Abstract: SUPERSONIC FAN BLADE A swept leading edge blade (10) rotates in a stream of air (26) and experiences supersonic relative air velocities over at least a portion of the blade surface. The maximum camber points (28, 40) of adjacent blade segments (20, 18) are located to prevent intensification of the compression wave generated by each segment (20, 18).

公开(公告)号：AU8049987A

公开(公告)日：1988-05-05

申请号：AU8049987

申请日：1987-10-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WEINGOLD HARRIS D ,  HARVEY WALTER B

IPC: F04D29/38 ,  B64C11/18 ,  F01D5/14 ,  F04D21/00

Abstract: A swept leading edge blade (10) rotates in a stream of air (26) and experiences supersonic relative air velocities over at least a portion of the blade surface. The maximum camber points (28, 40) of adjacent blade segments (20, 18) are located to prevent intensification of the compression wave generated by each segment (20, 18).

公开(公告)号：DE69026811T2

公开(公告)日：1996-09-12

申请号：DE69026811

申请日：1990-12-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WEINGOLD HARRIS D ,  POTTER GLEN E ,  BEHLKE ROY F ,  ANDY JOHN G ,  NEUBERT ROBERT J

IPC: F01D9/02 ,  F01D5/14 ,  F04D29/54

Abstract: An airfoil for a compression section of a rotary machine is disclosed. Various construction details are developed to increase the efficiency of the compression section. In one detailed embodiment, the airfoil has a spanwise axis or stacking line which extends in a generally radial direction. The stacking line or spanwise axis is straight over the mid-section of the airfoil and is angled circumferentially toward the radial direction in the end wall regions 58, 66 of the airfoil.

公开(公告)号：DE69026811D1

公开(公告)日：1996-06-05

申请号：DE69026811

申请日：1990-12-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WEINGOLD HARRIS D ,  POTTER GLEN E ,  BEHLKE ROY F ,  ANDY JOHN G ,  NEUBERT ROBERT J

IPC: F01D9/02 ,  F01D5/14 ,  F04D29/54

Abstract: An airfoil for a compression section of a rotary machine is disclosed. Various construction details are developed to increase the efficiency of the compression section. In one detailed embodiment, the airfoil has a spanwise axis or stacking line which extends in a generally radial direction. The stacking line or spanwise axis is straight over the mid-section of the airfoil and is angled circumferentially toward the radial direction in the end wall regions 58, 66 of the airfoil.

公开(公告)号：AU601502B2

公开(公告)日：1990-09-13

申请号：AU8049987

申请日：1987-10-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WEINGOLD HARRIS D ,  HARVEY WALTER B

IPC: F04D29/38 ,  B64C11/18 ,  F01D5/14 ,  F04D21/00

Abstract: A swept leading edge blade (10) rotates in a stream of air (26) and experiences supersonic relative air velocities over at least a portion of the blade surface. The maximum camber points (28, 40) of adjacent blade segments (20, 18) are located to prevent intensification of the compression wave generated by each segment (20, 18).