General Electric Company

Phoenix Motor, Inc.

Proterra Inc.

General Electric Technology Gmbh

James Harper

Yon Han Chong

Charlie Edmond Jones

Matthew Bernard Wilson

Gilbert Otto Kraemer

Robert Wade Clifford

Neal William Grooms

David Lai

Kevin Myers

Benjamin Robert Ryan

Akilez Krishnamurthy Arthanari

Geoffrey David Myers

Wei A Chen

David August Snider

Joseph Vincent Citeno

William Lawrence Byrne

Douglas Edward Dean

Abhijit Prabhakar Kulkarni

Mihir Kumar Lal

Daniel Robert Tegel

Stephen R Watts

Xiaoguang Yu

Eric Motter

Kevin Rodden

Scott Hall

Akilezkrishnamurthy Arthanari

Mathew B Wilson

Sergey Maskhuth Khayrulin

James Christopher Butts

Dmitry Alexandrovich Lysenko

Systems and methods of controlling temperature in a cabin of an electric vehicle that has an HVAC system powered by a battery system and an auxiliary heating system. Upon determining, by a system controller, that a setpoint temperature is less than or equal to a sensed cabin temperature while operating in an HVAC electric heat state, an auxiliary heat state, or a maximum heat state, automatically transitioning to an off state from the HVAC electric heat state, the auxiliary heat state, or the maximum heat state.

Systems and methods for managing multiple vehicle cabin heat sources and multiple controllers

A temperature control system for an electric vehicle includes a cabin temperature control system configured to control flow of a refrigerant through one or more heat exchangers to control a temperature of a cabin of the electric vehicle, a battery temperature control system configured to control the flow of a coolant through one or more heat exchangers to control a temperature of a battery system of the electric vehicle, and a power electronics temperature control system configured to control the flow of coolant through one or more heat exchangers to control a temperature of one or more power electronics. In a first configuration of the temperature control system, the battery temperature control system and the power electronics temperature control system may be thermally isolated, and, in a second configuration, the battery temperature control system and the power electronics temperature control system may thermally interact.

Temperature management systems and methods for electric vehicle

The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.

Premixed pilot nozzle for gas turbine combustor

An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.

Fuel injection assemblies for axial fuel staging in gas turbine combustors

A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.

Axial fuel staging system for gas turbine combustors

This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor.

Model-less combustion dynamics autotune

A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.

Thimble assemblies for introducing a cross-flow into a secondary combustion zone

A system includes a combustor assembly which receives a fuel-oxidant mixture. The system includes a control valve which controls a fuel flow into the combustor assembly. The system includes one or more sensors which measure one or more properties. The system includes a controller communicatively coupled to the one or more sensors and the control valve. The controller receives data from the one or more sensors indicative of operating conditions of the combustor assembly. The controller determines a predicted fuel flow for a first fuel line of a plurality of fuel lines based in part on the data received from the one or more sensors. The controller calculates a difference between a commanded fuel flow and the predicted fuel flow. The controller adjusts an operation of the control valve associated with a gas turbine engine when the difference is greater than a threshold.

Systems and methods for predicting fuel circuit leaks

A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.

Pilot premix nozzle and fuel nozzle assembly

In one embodiment, a system is provided. The system includes a turbine control system, comprising a processor. The processor is configured to receive an input for transitioning between a normal load path (NLP) of a turbine system and a cold load path (CLP) of the turbine system. The processor is additionally configured to determine a carbon monoxide (CO) setpoint based on the input. The processor is further configured to apply a temperature control based on the CO setpoint, wherein the normal load path comprises higher emissions temperatures as compared to the cold load path.

Transient emission temperature control of turbine systems

A method and apparatus for a diffusion tip for use with a fuel nozzle is described. The diffusion tip has a substantially circular body including an outer surface and an opposite inner surface. The diffusion tip body extends from a discharge end to an inlet end. The diffusion tip includes an inlet surface adjacent to the discharge end and defined within the body. A discharge surface is defined opposite the inlet surface. A plurality of diffusion apertures each extend between the discharge surface and the inlet surface, each aperture is oriented relative to the body to discharge a diffusion flow outward therefrom at an angle &#x3b3; (gamma) measured in an X-Z plane between a centerline of the aperture and an X-axis extending tangentially to the outer surface, and at an angle &#x3b8; (theta) measured in a Y-Z plane between the centerline of the aperture and a Y-axis extending radially outward from the centerline.

Method and apparatus to facilitate cooling of a diffusion tip within a gas turbine engine

Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.

Growing community of inventors

Greenville, SC, United States of America

James Harper