公开(公告)号：US10450873B2

公开(公告)日：2019-10-22

申请号：US15664996

申请日：2017-07-31

Applicant: Rolls-Royce Corporation

Inventor： Brett Barker ,  Bruce Varney ,  Brian Shoemaker ,  Charles Bulgrin

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D5/14

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

公开(公告)号：US20190032493A1

公开(公告)日：2019-01-31

申请号：US15664996

申请日：2017-07-31

Applicant: Rolls-Royce Corporation

Inventor： Brett Barker ,  Bruce Varney ,  Brian Shoemaker ,  Charles Bulgrin

IPC: F01D5/18 ,  F01D9/06

CPC classification number: F01D5/186 ,  F01D5/147 ,  F01D5/189 ,  F01D9/042 ,  F01D9/065 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2300/6033

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.

公开(公告)号：US20200080426A1

公开(公告)日：2020-03-12

申请号：US16580784

申请日：2019-09-24

Applicant: Rolls-Royce Corporation

Inventor： Brett Barker ,  Bruce Varney ,  Brian Shoemaker ,  Charles Bulgrin

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04

Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.