公开(公告)号：US20240426245A1

公开(公告)日：2024-12-26

申请号：US18213667

申请日：2023-06-23

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jeffrey T. Morton ,  Andrew E. Breault

IPC: F02C7/143 ,  F02C7/22 ,  F04D29/16 ,  F04D29/68

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a bladed rotor, a shroud and an actuation system. The bladed rotor includes a rotor base and a plurality of rotor blades arranged circumferentially around and connected to the rotor base. The shroud is adjacent tips of the rotor blades. The actuation system includes a water source and an actuator coupled to the shroud. The actuation system is configured to direct a quantity of water from the water source to the actuator to control clearance between the shroud and the tips of the rotor blades.

公开(公告)号：US20240302101A1

公开(公告)日：2024-09-12

申请号：US18119130

申请日：2023-03-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder

IPC: F28D7/00 ,  F28F9/02

CPC classification number: F28D7/0058 ,  F28F9/02

Abstract: A heat exchanger is provided that a flowpath extending longitudinally through a duct. The flowpath extends laterally within the duct between a first sidewall and a second sidewall. The flowpath extends vertically within the duct between a first manifold wall and a second manifold wall. The first manifold wall is configured to form a peripheral boundary of a first manifold plenum outside of the duct. The second manifold wall is configured to form a peripheral boundary of a second manifold plenum outside of the duct. A plurality of tubes extend vertically across the flowpath and are connected to the first manifold wall and the second manifold wall. Each of the tubes has a bore configured to fluidly couple the first manifold plenum to the second manifold plenum. The tubes include a first tube and a second tube. The first tube is adjacent and angularly offset from the second tube.

公开(公告)号：US20240301823A1

公开(公告)日：2024-09-12

申请号：US18119154

申请日：2023-03-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder ,  Neil J. Terwilliger

IPC: F02C6/18

CPC classification number: F02C6/18 ,  F05D2240/35 ,  F05D2260/213

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The recovery system includes an evaporator module and a condenser module. The condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

公开(公告)号：US12055067B2

公开(公告)日：2024-08-06

申请号：US18183079

申请日：2023-03-13

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/14 ,  F01D5/08 ,  F01D5/18 ,  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：US20240018875A1

公开(公告)日：2024-01-18

申请号：US18187839

申请日：2023-03-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan P. Dube ,  Wojciech Lipka

IPC: F01D9/04 ,  F01D5/18

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/041 ,  F01D5/284

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has 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 that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.

公开(公告)号：US11725816B2

公开(公告)日：2023-08-15

申请号：US17838032

申请日：2022-06-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Steven D. Porter

IPC: B23P15/00 ,  F02C7/18 ,  F23R3/06 ,  F23R3/00 ,  F23R3/50

CPC classification number: B23P15/00 ,  F02C7/18 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R3/007

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：US20230235699A1

公开(公告)日：2023-07-27

申请号：US17584909

申请日：2022-01-26

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Paul R. Hanrahan

IPC: F02C7/12 ,  B64D33/08 ,  F28D7/00

CPC classification number: F02C7/12 ,  B64D33/08 ,  F28D7/0041 ,  F05D2260/213

Abstract: An aircraft heat exchanger system according to an exemplary embodiment of this disclosure, among other possible things includes a first heat exchanger assembly that is disposed in an inlet duct assembly, and a skin heat exchanger assembly is in thermal communication with an outer surface of an aircraft structure. The skin heat exchanger is in fluid communication with the first heat exchanger such that a working fluid is communicated therebetween.

公开(公告)号：US11668199B2

公开(公告)日：2023-06-06

申请号：US17193369

申请日：2021-03-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Chang Gao

IPC: F01D9/00 ,  F01D9/04 ,  F02C3/04

CPC classification number: F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2300/6033

Abstract: A vane arc segment includes an airfoil fairing that has first and second platforms and an airfoil section. The platforms have first and second openings that open into the airfoil section. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side. The first platform has a first flange that projects radially from the non-gaspath side aft of the first opening and a second flange that projects radially from the non-gaspath side forward of the first opening. The first and second flanges are exclusive flanges on the first platform. The second platform has a third flange that projects radially from the non-gaspath side aft of the second opening.

公开(公告)号：US11448096B2

公开(公告)日：2022-09-20

申请号：US17150252

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D25/28 ,  F01D9/04 ,  F02C3/04

Abstract: A support system for an airfoil piece in a gas turbine engine includes first and second support platforms for supporting the airfoil piece there between. Each of the support platforms defines a forward support platform side, an aft support platform side, a first support platform circumferential side, a second support platform circumferential side, an airfoil side, and a non-airfoil side. The airfoil side of at least one of the support platforms has a radial channel therein for receiving a complementary radial flange of the airfoil piece. Each radial channel includes a radial channel first leg portion extending adjacent the aft support platform side, a radial channel second leg portion that extends from the radial channel first leg portion and that curves toward the forward support platform side, and a radial channel third leg portion that extends from the second leg portion toward the forward support platform side.

公开(公告)号：US20220082024A1

公开(公告)日：2022-03-17

申请号：US17023471

申请日：2020-09-17

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Tyler G. Vincent

IPC: F01D9/02 ,  F02C3/04

Abstract: A vane includes a ceramic airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side. The ceramic airfoil section has an internal cavity. A support spar extends through the internal cavity for supporting the ceramic airfoil section. The support spar is spaced from the airfoil wall such that there is a gap there between. The support spar has an internal through-passage that is fluidly isolated from the gap in the ceramic airfoil section. A baffle is disposed in the gap and is spaced apart from the airfoil wall and the support spar so as to divide the gap into a plenum space between the support spar 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.