General Electric Company

Cummins Enterprise LLC

Sap Se

Ge Infrastructure Technology, LLC

General Electric Company Polska Sp. Z O.o.

General Electric Renovables Espa&#xd1;a, S.l.

Ge Digital Holdings LLC

Honggang Wang

Michael Anthony Benjamin

Richard Louis Hart

Seung-Hyuck Hong

Ralph Teichmann

Anil Raj Duggal

Patrick Hammel Hart

Andrew Philip Shapiro

Sumit Bose

Xiangdong Kong

Radislav Alexandrovich Potyrailo

Narendra Digamber Joshi

Masoud Abbaszadeh

Darren Bawden Hickey

Philip Joseph Hart

John Guido Piccirillo

Brandon Wayne Miller

Randy M Vondrell

Hendrik Pieter Jacobus De Bock

Yao Liang Chen

Weizhong Yan

Kum Kang Huh

Mustafa Tekin Dokucu

Andrew Joseph Wickersham

Keith Garrette Brown

Alistair Martin Waddell

Liwei Hao

Lijun He

Hanchao Liu

Ryan St Pierre

Rebecca Dinan Zoracki

Harry Kirk Mathews, Jr

Trevor Howard Wood

Kishore Ramakrishnan

Karim Younsi

Biao Fang

Di Pan

Stefan Joseph Cafaro

Eric Richard Westervelt

Chaitanya Ashok Baone

Yingneng Zhou

Matthew Joseph Alinger

David Kelly Moyeda

Timothy Richard DePuy

Wei Zhou

Shih-Yang Hsieh

Anup Menon

Xingtian Shi

Arvind Kumar Tiwari

Fengcheng Sun

Manu Parashar

Philippe Nemery

Zhilin Wu

Baoming Huang

Lihan He

Yichao Zhang

Koji Asari

Yan Tan

Todd Michael Striker

Yuanyuan Cen

Shiguang Li

Miaolei Shao

Guang Xu

Willard Monten Wiseman

Yuh-Shyang Wang

Junqiang Zhou

Yingbin Zheng

Irene Chen

Kaveri Mahapatra

Juan Sanchez-Gasca

Shruti Dwarkanath Rao

Radhakrishnan Srinivasan

Andrew Philp Shapiro

Virginie Peron

Alexandre Lagarde

Raphael De Rocca-Serra

Mohammad Attia

Nan Xu

Patrick Carroll

Terry Wang

Pengyuan Wang

Mark Finch

An environmental control system assembly for an aircraft is provided. The assembly includes: an environmental control system; a fuel cell assembly in electrical communication with the environmental control system for providing electrical power to the environmental control system; and a controller operably connected to the fuel cell assembly, the controller operable to modulate an amount of power generated by the fuel cell assembly and provided to the environmental control system based on load forecasting data from an ECS load forecasting module of the controller.

Environmental control system having a fuel cell assembly

A method for operating a propulsion system for an aircraft, the propulsion system including a gas turbine engine and a fuel cell assembly, the fuel cell assembly including a fuel cell stack having a fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method including: executing a startup sequence for the fuel cell assembly, wherein executing the startup sequence for the fuel cell assembly includes initiating the startup sequence for the fuel cell assembly; executing a startup sequence for the gas turbine engine, wherein executing the startup sequence for the gas turbine engine comprises initiating the startup sequence for the gas turbine engine subsequent to initiating the startup sequence for the fuel cell assembly; and operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.

Systems and method of operating a fuel cell assembly

A power generation system for an aircraft includes a first power source, a second power source, and a power dispatch module communicatively coupled with the first and second power sources. The power dispatch module includes a controller having one or more processors configured to perform a plurality of operations, including but not limited to receiving a plurality of loading data associated with the power generation system, predicting a future power demand due to future load changes using the loading data, determining first and second power setpoints for the first and second power sources, respectively, based on the future power demand due to the future load changes, and controlling first and second power outputs of the first and second power sources based on the first and second power setpoints such that the future power demand of the power generation system is shared by the first and second power sources.

Power dispatch control system for multiple power generation sources

An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.

Gas turbine engine noise reduction

A dynamic simulation engine, having system parameters, may be provided for a component of an electrical power system (e.g., a generator, wind turbine, etc.). A model parameter tuning engine may receive, from a measurement data store, measurement data measured by an electrical power system measurement unit (e.g., a phasor measurement unit or digital fault recorder measuring a disturbance event). The model parameter tuning engine may then pre-condition the measurement data and set-up an optimization problem based on a result of the pre-conditioning. The system parameters of the dynamic simulation engine may be determined by solving the optimization problem with an iterative method until at least one convergence criteria is met. According to some embodiments, solving the optimization problem includes a Jacobian approximation that does not call the dynamic simulation engine if an improvement of residual meets a pre-defined criteria.

Power system measurement based model calibration with enhanced optimization

A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both.

Gas turbine engine and fuel cell assembly

A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.

An integrated fuel cell and combustor assembly includes a combustor that is fluidly coupled with at least one upstream compressor that generates compressed air. A fuel cell stack having a cathode and an anode is fluidly coupled to the combustor. The fuel cell stack is configured to receive intake fuel and a portion of the compressed air as intake air, to generate a fuel cell power output using the intake fuel and the intake air, and to direct a fuel and air exhaust from the fuel cell stack into the combustor. A self-reliant air supply system is fluidly coupled with the at least one upstream compressor and the fuel cell stack, and is configured to supply the intake air to the fuel cell stack. A fault-tolerant controller is configured to detect a transient event within the combustor and to control the self-reliant air supply system during the transient event.

Integrated fuel cell and combustor assembly

A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and defines a combustion chamber the combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack that has a plurality of fuel cells each extending between an inlet end and an outlet end. The inlet end receives a flow of air and fuel and the outlet end provides output products to the combustion chamber. The fuel cell assembly further includes an electrical circuit that is electrically coupled to the plurality of fuel cells and that extends through the casing.

Gas turbine combustion section having an integrated fuel cell assembly

A method for monitoring at least one rotor blade of a wind turbine includes implementing, via a controller, a control scheme for monitoring blade damage of the at least one rotor blade. The control scheme includes monitoring at least one electrical condition of a pitch system of the wind turbine. The method also includes converting the electrical condition(s) of the pitch system into a frequency domain. Further, the method includes determining one or more peaks of the frequency domain around a frequency component related to a natural frequency of the rotor blade. Moreover, the method includes determining a frequency deviation between the one or more peaks of the frequency domain and the frequency component related to the natural frequency of the rotor blade. As such, a frequency deviation outside of a predetermined frequency range is indicative of a rotor blade anomaly. Thus, the method includes implementing a control action when the frequency deviation is outside of the predetermined frequency range.

System and method for monitoring rotor blade health of a wind turbine

A propulsion system including: a fuel cell assembly having a fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from an aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including receiving data indicative of a mid-flight flameout within the combustion section; modifying the fuel cell assembly operating condition in response to receiving data indicative of the mid-flight flameout within the combustion section; and initiating a relight of the combustion section.

Relight of a propulsion system with a fuel cell

A method is provided for operating a propulsion system having a gas turbine engine and a fuel cell assembly. The fuel cell assembly includes a fuel cell. The method includes: receiving gas composition data of output products from the fuel cell; and controlling operation of the fuel cell assembly, the gas turbine engine, or both in response to the received gas composition data of the output products from the fuel cell.

Systems and method of operating a fuel cell assembly, a gas turbine engine, or both

A propulsion system is provided including: a propulsor; a turbomachine operable to drive the propulsor to generate thrust during operation; a fuel cell assembly configured to add power to the propulsor, the turbomachine, or both; and a multi-gas sensor operable with the turbomachine, the fuel cell assembly, or both for sensing gas composition data of a fluid flow in or to the turbomachine, the fuel cell assembly, or both, the gas composition data comprising data indicative of at least two gases and their concentrations.

An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, and a pre-burner system fluidly connected to the fuel cell stack. The fuel cell stack is configured to direct fuel and air exhaust from the fuel cell stack into the combustor. The pre-burner system is configured to control a temperature of an air flow directed into the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine. The engine assembly can further include a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack. The catalytic partial oxidation convertor is configured to develop a hydrogen rich fuel stream to be directed into the fuel cell stack.

Integrated fuel cell and engine combustor assembly

Systems and methods include a fuel cell stack extended around a combustion chamber that is configured to provide output products to the combustion chamber to achieve at least one of late lean injection and a desired combustor gas concentration distribution. The fuel cell stack is positioned at a downstream section of the combustion chamber along an axial direction.

Systems and methods for providing output products to a combustion chamber of a gas turbine engine

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Honggang Wang