公开(公告)号：US11905854B2

公开(公告)日：2024-02-20

申请号：US17971999

申请日：2022-10-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Jon E. Sobanski

IPC: F01D9/06 ,  B33Y80/00 ,  F01D5/18 ,  B22F5/00 ,  B22F5/04 ,  B22F10/28 ,  B23P15/04

CPC classification number: F01D9/065 ,  B22F10/28 ,  B23P15/04 ,  B33Y80/00 ,  F01D5/18 ,  F01D5/189 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2230/60 ,  F05D2300/6033

Abstract: An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

公开(公告)号：US20240018871A1

公开(公告)日：2024-01-18

申请号：US18183079

申请日：2023-03-13

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/14 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/081 ,  F01D5/14 ,  F01D5/147 ,  F01D5/18 ,  F01D5/282 ,  F01D9/041 ,  F05D2220/323 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/2214 ,  F05D2300/601 ,  F05D2300/603

Abstract: A method of fabricating a fiber-reinforced airfoil ring includes providing a mandrel that has a mandrel suction side and mandrel pressure side, and forming an endless braid around the mandrel. The endless braid conforms to the mandrel suction side and the mandrel pressure side. The endless braid is then consolidated with a matrix material. The mandrel is then removed, leaving the consolidated endless braid as a fiber-reinforced airfoil ring that has a suction side wall that extends between inner and outer platforms, a pressure side wall that extends between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction side wall and the pressure side wall, and at least one of the suction or pressure side mate faces includes protrusions along a trailing edge.

公开(公告)号：US20230242267A1

公开(公告)日：2023-08-03

申请号：US17587638

申请日：2022-01-28

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Thomas G. Tillman ,  Stuart S. Ochs

IPC: B64D33/02 ,  B64D27/24 ,  B64D27/10 ,  B64D33/10

CPC classification number: B64D33/02 ,  B64D27/24 ,  B64D27/10 ,  B64D33/10 ,  B64D2033/024 ,  B64D2027/026

Abstract: An aircraft propulsion system includes a propulsive fan assembly configured for assembly into an aircraft structure, the propulsive fan assembly that includes a fan rotatable about a fan axis, an inlet duct assembly disposed within the aircraft fuselage, the inlet duct assembly that includes an upper inlet duct with an upper inlet opening and a lower inlet duct with a lower inlet opening. The upper inlet duct and the lower inlet duct merge into a common inlet duct forward of the propulsive fan assembly, and an outlet duct is disposed aft of the propulsive fan assembly.

公开(公告)号：US20230159175A1

公开(公告)日：2023-05-25

申请号：US17535200

申请日：2021-11-24

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Paul R. Hanrahan ,  Joseph B. Staubach ,  Jill Klinowski

IPC: B64D27/24 ,  B64D27/26 ,  B64D29/02 ,  B64C39/10 ,  B64C11/28

CPC classification number: B64D27/24 ,  B64D27/26 ,  B64D29/02 ,  B64C39/10 ,  B64C11/28 ,  B64D2027/262

Abstract: A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.

公开(公告)号：US20230076312A1

公开(公告)日：2023-03-09

申请号：US17838032

申请日：2022-06-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Steven D. Porter

IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06 ,  F23R3/50

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

公开(公告)号：US11536147B2

公开(公告)日：2022-12-27

申请号：US17216973

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D11/00

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

公开(公告)号：US20220316350A1

公开(公告)日：2022-10-06

申请号：US17216973

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D11/00

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

公开(公告)号：US11415009B2

公开(公告)日：2022-08-16

申请号：US17150184

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan H. Farrar

IPC: F01D9/04 ,  F02C3/04

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section extending there between. There is a spar having a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion with a clevis mount that that protrudes from the second fairing platform. A support platform adjacent the second fairing platform has first and second through-holes. The end portion of the spar leg extends through the first through-hole and a pin extends though the clevis mount to lock the support platform to the spar leg. A stabilizer rod extends through the second through-hole of the support platform and limits rotation of the support platform about the pin.

公开(公告)号：US20220228499A1

公开(公告)日：2022-07-21

申请号：US17150184

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan H. Farrar

IPC: F01D9/04 ,  F02C3/04

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section extending there between. There is a spar having a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion with a clevis mount that that protrudes from the second fairing platform. A support platform adjacent the second fairing platform has first and second through-holes. The end portion of the spar leg extends through the first through-hole and a pin extends though the clevis mount to lock the support platform to the spar leg. A stabilizer rod extends through the second through-hole of the support platform and limits rotation of the support platform about the pin.

公开(公告)号：US11359497B1

公开(公告)日：2022-06-14

申请号：US17128355

申请日：2020-12-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Tyler G. Vincent

IPC: F01D5/18 ,  F01D9/04

Abstract: A vane arc segment includes an airfoil section, a spar, and a baffle. The spar supports the airfoil section and has a leg that extends in an internal cavity of the airfoil section. The leg is spaced from the airfoil wall such that there is a gap there between. The baffle divides the gap into a plenum space between the leg and the baffle and an impingement space between the baffle and the airfoil wall. The baffle has impingement holes directed toward the airfoil wall that connect the plenum space and the impingement space. The impingement space is of substantially uniform thickness and the plenum space is of non-uniform thickness along a portion of the span length of the airfoil section.