-
公开(公告)号：US20250154878A1
公开(公告)日：2025-05-15
申请号：US18935978
申请日：2024-11-04
Applicant: RTX Corporation
Inventor： William K. Ackermann
Abstract: A gas turbine engine includes a rotor having a plurality of blades without an outer housing, and rotating with a nose cone. The rotor, plurality of blades and nose cone provide a rotating structure. A static heat exchanger is positioned within the nose cone and a system for using a working fluid. An inlet from the system is connected to the heat exchanger and an outlet from the heat exchanger is connected back to the system. A central opening is in a central portion of the nose cone to deliver cooling air across the heat exchanger. A duct downstream of the heat exchanger directs the cooling air such that the cooling air can move radially outwardly through the rotating structure such that the cooling air can be directed into a propulsion airflow path. A method and a heat exchange system are also disclosed.
-
公开(公告)号：US20250116224A1
公开(公告)日：2025-04-10
申请号：US18376699
申请日：2023-10-04
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Michael G. McCaffrey
Abstract: A particle separator configured to be disposed within a turbine engine diffuser flow path is provided. The particle separator includes a housing, a hollow cavity member, and a helical member. The housing has a forward end inlet, an exterior wall, an aft wall, an interior cavity, and an aft exhaust passage extending outwardly from the exterior wall adjacent the aft wall. The hollow cavity member has a first portion, an interior region, and an open aft end. The first portion is disposed within the housing interior cavity and includes perforations. The helical member is disposed within the housing interior cavity. The helical member forms a helical passage between the housing exterior wall and the first portion of the hollow cavity member. The helical passage has a passage inlet disposed adjacent to the housing forward end inlet and a terminal end in communication with the aft exhaust passage.
-
3.发明申请公开(公告)号：US20240401500A1
公开(公告)日：2024-12-05
申请号：US18420862
申请日：2024-01-24
Applicant: RTX CORPORATION
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.
-
Patent Agency Ranking
4.发明申请公开(公告)号：US20250154901A1
公开(公告)日：2025-05-15
申请号：US18934682
申请日：2024-11-01
Applicant: RTX Corporation
Inventor： William K. Ackermann
Abstract: A gas turbine engine includes an open rotor configured to rotate with a nose cone. A heat exchanger is positioned within the nose cone and a system for using a working fluid. An inlet from the system is connected to the heat exchanger and an outlet from the heat exchanger connected back to the system. A central opening is in a central portion of the nose cone to deliver cooling air across the heat exchanger, and a duct downstream of the heat exchanger to direct the cooling air radially to at least one static opening such that the cooling air can move radially outwardly through static structure and be directed into a propulsion airflow path. A method and a heat exchange system are also disclosed.
-
5.发明公开公开(公告)号：US20240353105A1
公开(公告)日：2024-10-24
申请号：US18639359
申请日：2024-04-18
Applicant: RTX Corporation
Inventor： Thomas E. Clark , Andrew E. Breault , William K. Ackermann
CPC classification number: F23R3/60 , F23R3/002 , F23R3/50 , F23R2900/00017
Abstract: A gas turbine engine is provided having an axial centerline, a compressor section, a turbine section, and a combustor section. The turbine section has a turbine first vane assembly that includes an annular first vane inner radial support. The combustor section has an outer casing, an annular combustor, and a unitary inner diffuser structure. The annular combustor has an inner radial flange. The unitary inner diffuser structure includes a compressor discharge, an inner diffuser case, and a tangential onboard injector (TOBI) inseparably attached to one another. The unitary inner diffuser structure further includes an outer radial flange and a TOBI connection flange. The annular FV inner radial support, the combustor inner radial flange, and the TOBI connection flange are secured to one another.
-
公开(公告)号：US20250116227A1
公开(公告)日：2025-04-10
申请号：US18376706
申请日：2023-10-04
Applicant: RTX Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Michael G. McCaffrey , Paul R. Hanrahan
Abstract: A particle separator configured to be disposed within a turbine engine diffuser flow path is provided. The particle separator includes a housing that extends between a forward end and an aft end, first and second swirl vane stages, and first and second air flow exits. The first swirl vane stage is configured to cause an air flow passing through the first swirl vane stage to swirl within the housing as the air flow travels axially in a direction from the forward end toward the aft end of the housing. The second swirl vane stage is configured to cause a first portion of the air flow passing through the second swirl vane stage to redirect into a substantially axially directed flow that enters the second air flow exit.
-
公开(公告)号：US20250059892A1
公开(公告)日：2025-02-20
申请号：US18235402
申请日：2023-08-18
Applicant: RTX Corporation
Inventor： William K. Ackermann
IPC: F01D5/08
Abstract: A tie-shaft with thermal barrier coating system including a tie-shaft including an inside diameter and an outside diameter opposite the inside diameter, an exterior surface proximate the outside diameter; a piston-ring seal in operative communication with the tie-shaft proximate the outside diameter; and the thermal coating system disposed on the exterior surface of the tie-shaft proximate the piston-ring seal.
-
公开(公告)号：US20240353104A1
公开(公告)日：2024-10-24
申请号：US18639450
申请日：2024-04-18
Applicant: RTX Corporation
Inventor： William K. Ackermann , Thomas E. Clark , Andrew E. Breault
CPC classification number: F23R3/005 , F02C7/14 , F23R3/002 , F05D2240/35 , F05D2260/211 , F05D2260/213
Abstract: A gas turbine engine is provided that includes compressor and combustor sections, inner and outer casings, an annular diffuser, an inner diffuser casing, a heat exchanger, and an HPT stator vane stage. An annular combustor is disposed radially inward of the outer casing and has inner and outer radial wall structures. The outer casing and the combustor outer radial wall structure define a diffuser OD flow path. The annular diffuser directs diffuser gas towards the combustor section. The inner diffuser casing is disposed radially inward of the annular combustor and spaced apart from the combustor inner radial wall structure. The inner casing is disposed radially inward of and spaced apart from the inner diffuser casing. The inner diffuser casing and the inner casing define an ICF passage. The heat exchanger is configured to produce intercooler gas. Intercooler gas is directed through the ICF passage and into the HPT stator vanes.
-
-
-
-
-
-
-
Search Results
8
records
(took 0.011 seconds)
