公开(公告)号：AU2003274350A1

公开(公告)日：2004-05-13

申请号：AU2003274350

申请日：2003-10-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY ,  WAGNER JOEL

IPC: F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F04D29/54 ,  F04D29/68

Abstract: A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil by directing the cooler gas from the proximal end of the airfoil to the hotter gas at the medial section of the airfoil.

公开(公告)号：SG126736A1

公开(公告)日：2006-11-29

申请号：SG200306432

申请日：2003-10-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY A ,  WAGNER JOEL

IPC: F01D5/00 ,  F01D9/00

Abstract: A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil by directing the cooler gas from the proximal end of the airfoil to the hotter gas at the medial section of the airfoil.

公开(公告)号：NO20052477A

公开(公告)日：2005-07-19

申请号：NO20052477

申请日：2005-05-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY ,  WAGNER JOEL

IPC: F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F04D29/54 ,  F04D29/68 ,  F01D5/12

CPC classification number: F01D5/145 ,  F01D5/143 ,  F01D9/04 ,  F04D29/544 ,  F04D29/681 ,  F05D2250/14 ,  F05D2250/184 ,  F05D2250/71 ,  Y02T50/673 ,  Y10S415/914

公开(公告)号：CA2446035A1

公开(公告)日：2004-04-23

申请号：CA2446035

申请日：2003-10-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WAGNER JOEL ,  ZESS GARY A

IPC: F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F04D29/54 ,  F04D29/68 ,  F02C9/16 ,  F01D5/18

Abstract: A flow directing device of a gas turbine engine, comprising: an airfoil havi ng a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device al so reduces heat load on the airfoil by directing the cooler gas from the proximal end o f the airfoil to the hotter gas at the medial section of the airfoil.

公开(公告)号：PL376051A1

公开(公告)日：2005-12-12

申请号：PL37605103

申请日：2003-10-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY ,  WAGNER JOEL

IPC: F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F04D29/54 ,  F04D29/68

Abstract: A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil by directing the cooler gas from the proximal end of the airfoil to the hotter gas at the medial section of the airfoil.

公开(公告)号：NO20052477L

公开(公告)日：2005-07-19

申请号：NO20052477

申请日：2005-05-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY ,  WAGNER JOEL

IPC: F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F04D29/54 ,  F04D29/68 ,  F01D5/12

Abstract: A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil by directing the cooler gas from the proximal end of the airfoil to the hotter gas at the medial section of the airfoil.

公开(公告)号：NO20052477D0

公开(公告)日：2005-05-23

申请号：NO20052477

申请日：2005-05-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY ,  WAGNER JOEL

IPC: F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F04D29/54 ,  F04D29/68 ,  F01D

Abstract: A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading edge, along the suction and pressure sides, and towards the trailing edge. The device could be part of a vane segment. In addition to eliminating a horseshoe vortex, the device also reduces heat load on the airfoil by directing the cooler gas from the proximal end of the airfoil to the hotter gas at the medial section of the airfoil.