公开(公告)号：US20240392970A1

公开(公告)日：2024-11-28

申请号：US18652125

申请日：2024-05-01

Applicant: ROLLS-ROYCE plc

Inventor： Stephen C. HARDING

IPC: F23R3/42 ,  F02C3/14

Abstract: A combustor assembly for a gas turbine engine comprises a combustor casing. The combustor casing has a diametral height D and an axial length L. An Aspect Ratio parameter S is defined as: S = D L and the S parameter lies in the range of 0.30 to 1.00.

公开(公告)号：US12152532B2

公开(公告)日：2024-11-26

申请号：US18486362

申请日：2023-10-13

Applicant: RTX CORPORATION

Inventor： Joseph B. Staubach ,  Neil J. Terwilliger ,  Joseph E. Turney

IPC: F02C3/30 ,  F02C3/14 ,  F02C3/22 ,  F02C7/14

Abstract: A turbine engine assembly includes a condenser assembly arranged along the core flow path to extract water from the exhaust gas flow, and an evaporator assembly where thermal energy from the exhaust gas flow is communicated to the water extracted by the condenser assembly to generate a steam flow for injection into the core flow path. The evaporator assembly splits steam generation and cooling functions to increase efficiencies of each function.

公开(公告)号：US12110820B2

公开(公告)日：2024-10-08

申请号：US18241447

申请日：2023-09-01

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Steven Mazur ,  Rex M. Little

IPC: F02C3/14 ,  F01D25/12 ,  F02C3/08 ,  F02C6/08

CPC classification number: F02C3/14 ,  F01D25/12 ,  F02C3/08 ,  F02C6/08

Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

公开(公告)号：US20240280052A1

公开(公告)日：2024-08-22

申请号：US18649607

申请日：2024-04-29

Applicant: General Electric Company

Inventor： Joshua Tyler Mook ,  John Alan Manteiga ,  Christopher Williams

IPC: F02C7/06 ,  F01D25/16 ,  F01D25/24 ,  F02C3/14 ,  F02C7/18 ,  F02C7/20 ,  F04D29/053 ,  F04D29/056 ,  F04D29/32 ,  F04D29/54

CPC classification number: F02C7/06 ,  F01D25/162 ,  F01D25/246 ,  F02C3/14 ,  F02C7/18 ,  F02C7/20 ,  F04D29/053 ,  F04D29/056 ,  F04D29/321 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/35

Abstract: The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.

公开(公告)号：US11994296B2

公开(公告)日：2024-05-28

申请号：US18034119

申请日：2021-09-13

Applicant: MITIS S.A. ,  UNIVERSITE LIBRE DE BRUXELLES

Inventor： Michel Delanaye ,  Alessandro Parente

IPC: F23R3/00 ,  F02C3/14 ,  F23R3/16 ,  F23R3/54

CPC classification number: F23R3/16 ,  F02C3/14 ,  F23R3/54 ,  F05D2250/82

Abstract: A combustion device for an electricity production or energy cogeneration apparatus, the apparatus comprising a gas turbine supplied by the device, the device being suitable for a combustion regime of a “flameless” type, the device including: an outer tube; and a combustion tube forming a combustion zone for flameless combustion of a mixture of oxidizing air and fuel, the combustion tube being concentric with the outer tube, in communication with fuel-injection means, and with air-injection means arranged at a first end of the combustion tube, referred to as a front end, and which is closed by an end wall at a second end of the combustion tube, referred to as a rear end, the end wall being secured to the combustion tube and fluidtight, the fuel-injection means including at least a first orifice, referred to as a fuel-injection orifice, the air-injection means including at least a second orifice.

公开(公告)号：US20230399996A1

公开(公告)日：2023-12-14

申请号：US17838167

申请日：2022-06-11

Applicant: Isaac Erik Anderson

Inventor： Isaac Erik Anderson

IPC: F02K1/38 ,  F02C3/14 ,  F02C7/04

CPC classification number: F02K1/38 ,  F05D2220/323 ,  F02C7/04 ,  F02C3/14

Abstract: The engine described herein utilizes an internal low pressure near the nozzle to draw fluid through a center section/duct of the engine and therefore through an upstream, cold, turbine. The fluid moving through this center duct-section experiences a pressure differential between the zone of the incoming fluid (which raises pressure upstream) and the low pressure zone generated near the nozzle. With fast-moving fluid around each side of this cold turbine duct, inducing a Venturi effect on the fluid passing through the duct, a low pressure is generated and therefore enacts work on the turbine. Using this method, turbine blades are not down stream of the hot combustion section and therefore can be made with light weight and low melting temperature material. With a cold section turbine, the engine can therefore be considerably lighter and cheaper to manufacture and maintain.

公开(公告)号：US11841141B2

公开(公告)日：2023-12-12

申请号：US17072465

申请日：2020-10-16

Applicant: GE AVIO S.r.l ,  General Electric Company

Inventor： Massimo Giovanni Giambra ,  Joseph Douglas Monty ,  Stephen John Howell

IPC: F23R3/54 ,  F23R3/06 ,  F02C3/14 ,  F02C7/18 ,  F23R3/46 ,  F01D9/02 ,  F23R3/50

CPC classification number: F23R3/54 ,  F02C3/145 ,  F02C7/18 ,  F23R3/06 ,  F23R3/46 ,  F01D9/023 ,  F05D2220/323 ,  F05D2240/35 ,  F23R3/50 ,  F23R2900/00017

Abstract: An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

公开(公告)号：US11840958B2

公开(公告)日：2023-12-12

申请号：US17393508

申请日：2021-08-04

Applicant: RTX Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Christopher J. Hanlon

IPC: F02C6/02 ,  F02C3/10 ,  F02C7/36 ,  F02C3/14 ,  F02C7/04 ,  F02K3/04

CPC classification number: F02C3/10 ,  F02C6/02 ,  F02C7/36 ,  F02C3/14 ,  F02C7/04 ,  F02K3/04

Abstract: A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.

公开(公告)号：US11834994B2

公开(公告)日：2023-12-05

申请号：US17623021

申请日：2020-08-06

Applicant: Mitsubishi Power, Ltd.

Inventor： Saki Matsuo ,  Satoshi Hada ,  Tomoko Morikawa ,  Hiroyuki Otomo

IPC: F02C7/18 ,  F01D9/02 ,  F01D25/12 ,  F02C3/14 ,  F16J15/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/28

CPC classification number: F02C7/18 ,  F01D5/186 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F02C3/14 ,  F02C7/28 ,  F16J15/02 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/202

Abstract: A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.

公开(公告)号：US20230313996A1

公开(公告)日：2023-10-05

申请号：US17811762

申请日：2022-07-11

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Pradeep Naik

IPC: F23R3/42 ,  F02C3/14 ,  F02C7/00

CPC classification number: F23R3/42 ,  F02C7/00 ,  F02C3/14

Abstract: An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.