公开(公告)号：EP3783196A1

公开(公告)日：2021-02-24

申请号：EP20187983.0

申请日：2020-07-27

申请人： Raytheon Technologies Corporation

发明人： BALES, Daniel A. ,  NOVIKOV, Dmitri ,  DOLAN, Robert C. ,  MALMBORG, Eric W. ,  GORDON, Steven T.

IPC分类号： F01D5/14 ,  B23P15/04

摘要： An airfoil (261) for a gas turbine engine (20) according to an example of the present disclosure includes, among other things, a first portion (282) welded to a second portion (284) along an interface (286) such that at least the first portion (282) establishes an airfoil section (262) and the second portion (284) establishes a root section (264) mountable to a rotatable hub (45). The airfoil section (262) includes an airfoil body (268) extending between leading and trailing edges (LE, TE) in a chordwise direction (X), extending between pressure and suction sides (PS, SS) separated in a thickness direction (T), and extending from the root section (264) in a spanwise direction to a tip portion (266). A recessed region (278) extends inwardly from at least one of the pressure and suction sides (PS, SS). The airfoil body (268) includes at least one rib (74) bounding a respective pocket (72) within a perimeter (278P) of the recessed region (278). A cover skin (270) is welded to the airfoil body (268) along the at least one rib (74) to enclose the recessed region (278). A method of forming a gas turbine engine component (260) is also disclosed.

公开(公告)号：EP3734014A1

公开(公告)日：2020-11-04

申请号：EP20170117.4

申请日：2020-04-17

申请人： Raytheon Technologies Corporation

发明人： DOLAN, Robert C.

IPC分类号： F01D5/14 ,  B23K15/00 ,  B64C11/24

摘要： A method of forming an airfoil (100) includes the steps of (a) providing an airfoil body (106) with a hollow (102) having at least one rib (108) extending to an outer surface, and forming the outer surface of the rib (108) to have at least one groove (110) connecting a hollow pocket (112) within a boundary defined by the rib (108) to a location outwardly of the rib, (b) placing a cover (104) over the hollow (102), and (c) welding the cover (104) to the airfoil body (106), and such that the rib (108) is welded to the blade cover. An intermediate airfoil body (106) is also disclosed.

公开(公告)号：EP3789131A1

公开(公告)日：2021-03-10

申请号：EP20191544.4

申请日：2020-08-18

申请人： Raytheon Technologies Corporation

发明人： BALES, Daniel A. ,  DeMICHAEL, Thomas ,  DOLAN, Robert C. ,  PARISI, Francis B.

IPC分类号： B21D22/02 ,  B21D26/053 ,  B21D37/16 ,  B21D53/78 ,  C22C1/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  B23P15/04 ,  F01D5/14

摘要： A method of forming a gas turbine engine component (260) according to an example of the present disclosure includes, among other things, attaching a cover skin (270) to an airfoil body (268), the airfoil body (268) and the cover skin (270) cooperating to establish pressure and suction sides (PS, SS) of an airfoil (261), positioning the airfoil (261) between first and second dies (287-1, 287-2) of a deforming station (284-2), heating the airfoil body (268) to a first predefined temperature threshold between the first and second dies (287-1, 287-2), and moving the first die (287-1) relative to the second die (287-2) to hold the airfoil (261) between the first and second dies (287-1, 287-2) subsequent to the heating step, and then deforming the airfoil (261) between the first and second dies (287-1, 287-2).