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公开(公告)号：US11976633B2
公开(公告)日：2024-05-07
申请号：US17376965
申请日：2021-07-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Chaohong Cai , Timothy J Crowley , David Lei Ma , Richard P Meisner
CPC classification number: F03D7/043 , F03D7/0224 , F03D7/0272 , F03D7/0276 , F05B2270/327 , F05D2220/329
Abstract: A control system for limiting power turbine torque (QPT) of a gas turbine engine includes a controller including a processor and memory configured to control the gas turbine engine, the controller including an engine control module that provides an effector command signal to a gas generator of the gas turbine engine; a power turbine governor module that outputs a preliminary torque request (QPT_req_pre); and a power turbine torque (QPT) optimal limiter module that outputs a maximum torque topper (QPT_max) to limit a power turbine speed overshoot of the gas turbine engine; wherein the controller outputs a minimum value between the preliminary torque request (QPT_req_pre) and the maximum torque topper (QPT_max) to the engine control module.
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公开(公告)号：US20240026816A1
公开(公告)日：2024-01-25
申请号：US17871581
申请日：2022-07-22
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Walter A. Ledwith, JR. , Joseph B. Staubach , David Lei Ma
Abstract: An energy supply system includes a source of gas which is at a pressure that is equal to or greater than an atmospheric pressure. The source of gas is configured to deliver the gas into a combustor where it is mixed with a fuel. The combustor is also connected to receive a source of steam. The combustor is operable to provide combustion. Products of the combustion downstream of the combustor are connected to be delivered across a turbine rotor. The turbine rotor is provided with a shaft. The turbine shaft drives a generator. An evaporator downstream of the turbine receives the products of the combustion. The evaporator is operable to heat a source of water. The source of water downstream of the evaporator is the source of steam delivered into the combustor. The gas includes greater than 80% oxygen and the fuel includes hydrogen.
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公开(公告)号：US12259134B2
公开(公告)日：2025-03-25
申请号：US18342016
申请日：2023-06-27
Applicant: Raytheon Technologies Corporation
Inventor： Walter A. Ledwith, Jr. , David Lei Ma
Abstract: A propulsion system for an air vehicle includes a fan system that includes a fan that is coupled to a fan drive electric motor for generating a fan discharge airflow, an augmentor where fuel is mixed with a portion of the fan discharge airflow to generate a propulsive flow in a first operating configuration, a bypass duct for directing the fan discharge airflow into the augmentor, a duct blocker for selectively closing the bypass duct to the fan discharge airflow, a liquid oxygen system that is configured to inject liquid oxygen into the augmentor to mix with the fuel when the fan discharge airflow is closed by the duct blocker, the mixture of fuel flow and liquid oxygen generates the propulsive flow in a second operating configuration, and an electric power generation system is coupled to drive the fan drive electric motor.
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公开(公告)号：US20250003591A1
公开(公告)日：2025-01-02
申请号：US18342016
申请日：2023-06-27
Applicant: Raytheon Technologies Corporation
Inventor： Walter A. Ledwith, JR. , David Lei Ma
Abstract: A propulsion system for an air vehicle includes a fan system that includes a fan that is coupled to a fan drive electric motor for generating a fan discharge airflow, an augmentor where fuel is mixed with a portion of the fan discharge airflow to generate a propulsive flow in a first operating configuration, a bypass duct for directing the fan discharge airflow into the augmentor, a duct blocker for selectively closing the bypass duct to the fan discharge airflow, a liquid oxygen system that is configured to inject liquid oxygen into the augmentor to mix with the fuel when the fan discharge airflow is closed by the duct blocker, the mixture of fuel flow and liquid oxygen generates the propulsive flow in a second operating configuration, and an electric power generation system is coupled to drive the fan drive electric motor.
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公开(公告)号：US20230313735A1
公开(公告)日：2023-10-05
申请号：US17708095
申请日：2022-03-30
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Lance L. Smith , David Lei Ma , Joseph B. Staubach , Brian M. Holley , Sean C. Emerson
Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.
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Patent Agency Ranking
公开(公告)号：US20240151179A1
公开(公告)日：2024-05-09
申请号：US17980957
申请日：2022-11-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Steven W. Burd , Joseph B. Staubach , David Lei Ma
CPC classification number: F02C3/107 , F02C7/32 , F05D2220/323 , F05D2220/60 , F05D2240/35 , F05D2260/4031
Abstract: An aircraft power system includes an internal combustion core engine where an inlet airflow is mixed with a fuel and ignited to generate shaft power and a primary gas flow, a boost combustor where a portion of the primary gas flow from the core engine is combined with fuel and ignited to generate a boosted gas flow, and a drive turbine that includes a drive output shaft wherein the boosted gas flow is expanded to generate shaft power.
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公开(公告)号：US20240102416A1
公开(公告)日：2024-03-28
申请号：US17951879
申请日：2022-09-23
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： David Lei Ma , Joseph B. Staubach
IPC: F02C3/30
CPC classification number: F02C3/30 , F05D2220/32 , F05D2240/35 , F05D2270/08
Abstract: A turbine engine assembly includes a turbine section including at plurality of turbine stages through which the gas flow expands to generate a mechanical power output. An inter-turbine burner between at least two of the plurality of turbine stages reheats the gas flow. A condenser extracts water from the gas flow exhausted from the turbine section, and an evaporator heats the water extracted by the condenser to generate a steam flow with the steam flow communicated to the inter-turbine burner and added to the gas flow expanded through the turbine section.
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公开(公告)号：US11802508B2
公开(公告)日：2023-10-31
申请号：US17708095
申请日：2022-03-30
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Lance L. Smith , David Lei Ma , Joseph B. Staubach , Brian M. Holley , Sean C. Emerson
Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.
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公开(公告)号：US20230160347A1
公开(公告)日：2023-05-25
申请号：US18153487
申请日：2023-01-12
Applicant: Raytheon Technologies Corporation
Inventor： Timothy J. Crowley , Sorin Bengea , Manuj Dhingra , David Gelwan , Kevin Hendricks , Joshua Adams , Martin Richard Amari , Richard P. Meisner , David Lei Ma
CPC classification number: F02C9/00 , B64D27/02 , B64D2027/026 , F05D2220/76 , F05D2220/323 , F05D2240/60 , F05D2260/80 , F05D2270/09 , F05D2270/20 , F05D2270/44 , F05D2270/80
Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.
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公开(公告)号：US20210340956A1
公开(公告)日：2021-11-04
申请号：US17376965
申请日：2021-07-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Chaohong Cai , Timothy J. Crowley , David Lei Ma , Richard P. Meisner
Abstract: A control system for limiting power turbine torque (QPT) of a gas turbine engine includes a controller including a processor and memory configured to control the gas turbine engine, the controller including an engine control module that provides an effector command signal to a gas generator of the gas turbine engine; a power turbine governor module that outputs a preliminary torque request (QPT_req_pre); and a power turbine torque (QPT) optimal limiter module that outputs a maximum torque topper (QPT_max) to limit a power turbine speed overshoot of the gas turbine engine; wherein the controller outputs a minimum value between the preliminary torque request (QPT_req_pre) and the maximum torque topper (QPT_max) to the engine control module.
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