Hamilton Sundstrand Corporation

Benjamin T Harder

Matthew Allen Slayter

Jeff A Brown

Jeffrey Todd Roberts

James Vandung Nguyen

Paul F Fox

Daniel Richard Walker

Brian McMasters

Dwayne Leon Wilson

Richard Alan Davis

Edward W Goy

Adrian L Stoicescu

Richard R Hergert

William G Sheridan

Ryan Shook

Weishun William Ni

Thomas Jakab

Mark W Shoemaker

John T Pech

Weishun Willaim Ni

Mark W Showmaker

A combined air turbine starter and flow control valve includes a turbine having turbine blades and a shaft rotating with the turbine blades. The turbine is received within a nozzle housing. The nozzle housing includes an inlet. A radially outwardly extending inner surface extends from the inlet and toward the turbine blades. A flow control piston is received to be movable along a rotational axis of the turbine shaft, and toward and away the radially outwardly extending surface of the nozzle housing. A control is programmed to direct a movement system to position the flow control piston relative to the radially outwardly extending surface to achieve a desired volume of airflow to the turbine blades. A gas turbine engine starting system is also disclosed.

Combined control valve and air turbine starter

A variable displacement piston pump, having: a housing, a pivot assembly to pivot between minimal and maximum pivot angles; a pump cover defining an actuator bore with an actuator piston, an actuator arm extending from the actuator piston to the pivot assembly; and an electronic control unit (ECU) coupled to the pump, the ECU having: a pump controller, a linear variable differential transducer (LVDT) coupled to the pump controller and the actuator piston, and an electrohydraulic solenoid valve (EHSV) coupled to the pump controller, the ECU is configured to: determine a pivot differential for the pivot assembly between a target pivot angle and a current pivot angle; determine a position differential for the actuator piston, corresponding to the pivot differential of the pivot assembly; control the EHSV to move the actuator piston by the position differential; and determine, from the LVDT, that the actuator piston moved by the position differential.

Variable displacement piston pump with electronic control unit to provide direct metering control

A fuel supply system includes a pump to be connected to a fuel tank. A metering valve is downstream of the pump. A control is programmed to control at least one of the pump and metering valve. The control is operable to take in a flow demand signal and a fuel pressure signal from a controller associated with a gas turbine engine. The flow demand signal is indicative of a desired flow volume and the fuel pressure signal is indicative of a desired fuel pressure. Operation conditions are identified for the at least one of said pump and the metering valve. A gas turbine engine and fuel supply system is also disclosed.

Smart fuel supply system

A fuel pump system can include a motor and a pump connected to the motor. The pump can be configured to receive an inlet flow from an inlet line, to pressurize the inlet flow, and to output a pressurized flow to an output line for an engine. The system can include a bypass line disposed between the outlet line and the inlet line, and a bypass valve disposed on the bypass line and configured to allow pressurized flow to flow to the inlet line in an open state, and to prevent pressurized flow from flowing to the inlet line in a closed state. The bypass valve can be configured to allow pressurized flow to flow to the inlet line to circulate flow and to maintain a constant pressure on the output line.

Fuel pump systems

A method of manufacturing a motoring system for a gas turbine having the steps of: assembling a pinned mechanical fuse, the pinned mechanical fuse including at least one shear pin; forming an outer housing; installing a reduction gear train into the outer housing, the reduction gear train having an input and an output; operably connecting a motor to the input; operably connecting a clutch to the output using the pinned mechanical fuse, the clutch in operation engages and disengages the reduction gear train; operably connecting a starter to the clutch, the starter having an output shaft; and operably connecting an accessory gearbox to the output shaft of the starter. The clutch is operably connected to the accessory gearbox through the starter and the output shaft. The at least one shear pin in operation shears when torque on the pinned mechanical fuse is greater than or equal to a selected value.

Method for manufacturing a motoring system for a gas turbine engine

A method of manufacturing a motoring system for a gas turbine engine including the steps of: forming a mechanical shaft fuse, the mechanical shaft fuse including a plurality of through holes; forming an outer housing; installing a reduction gear train into the outer housing, the reduction gear train having an input and an output; operably connecting an electric motor to the input; operably connecting a clutch to the output using the mechanical shaft fuse, the clutch in operation engages and disengages the reduction gear train; operably connecting a starter to the clutch, the starter having an output shaft; and operably connecting an accessory gearbox to the output shaft of the starter. The mechanical shaft fuse in operation shears when torque on the mechanical is greater than or equal to a selected value.

Mechanical shear fuse for engine motoring system

According to an aspect, a system for a gas turbine engine includes a reduction gear train operable to drive rotation of a starter gear train that interfaces to an accessory gearbox of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train and a core-turning clutch operably connected to the starter interface gear. The reduction gear train also includes a planetary gear system operably connected to the core-turning clutch and a jacking gear system operably connected to the planetary gear system and a core-turning input.

Gas turbine engine starter reduction gear train with jacking and planetary geared transmission

According to an aspect, a system for a gas turbine engine includes a reduction gear train operable to drive rotation of a starter gear train that interfaces to an accessory gearbox of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train and a core-turning clutch operably connected to the starter interface gear. The reduction gear train also includes a geared rotary actuator including a primary planetary gear system, where the geared rotary actuator is operably connected to the core-turning clutch. The reduction gear train further includes a secondary planetary gear system operably connected to the primary planetary gear system and a core-turning input. The system also includes a mounting pad with an interface to couple a core-turning motor to the core-turning input of the reduction gear train.

Gas turbine engine starter reduction gear train with geared rotary actuator

A motoring system for a gas turbine engine having: a reduction gear train having an input and an output; an electric motor operably connected to the input; a clutch operably connected to the output, the clutch in operation engages and disengages the reduction gear train; and a mechanical shaft fuse operably connecting the output to the clutch, the mechanical shaft fuse in operation shears when torque on the mechanical shaft fuse is greater than or equal to a selected value. The mechanical shaft fuse includes a plurality of through holes.

A boost pump includes a housing cover and a pump housing engaged opposite to the housing cover. Volute passages are defined between the housing cover and the pump housing. The volute passages include a circumferentially extending volute defining a plurality of cross sections defined in a housing including the pump housing and the housing cover. The plurality of surfaces are defined as a set of dimensions set out in at least one of TABLES 1 through 3.

Volutes for engine mounted boost stages

A motoring system for a gas turbine engine having: a reduction gear train having an input and output; a motor operably connected to the input; a clutch operably connected to the output, the clutch in operation engages and disengages the reduction gear train; and a pinned mechanical fuse operably connecting the output to the clutch, the pinned mechanical fuse having at least one shear pin. The pinned mechanical fuse having: an outer sleeve having a first section, second section, inner chamber, outer wall, and at least one through hole connecting the inner chamber to the outer wall within the first section; and an inner sleeve having a first portion, second portion, outer surface, and at least one blind hole located in the outer surface within the second portion. The second portion being located within the inner chamber and operably connected to the outer sleeve through at least one shear pin.

Pinned mechanical fuse for engine motoring system

According to an aspect, a system for a gas turbine engine includes a reduction gear train operable to drive rotation of a starter gear train that interfaces to an accessory gearbox of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train, a core-turning clutch operably connected to the starter interface gear, and a plurality of stacked planetary gear systems operably connected to the core-turning clutch and a core-turning input. The system also includes a mounting pad including an interface to couple a core-turning motor to the core-turning input of the reduction gear train.

Gas turbine engine starter reduction gear train with stacked planetary gear systems

A boost pump includes a boost cover and a main pump housing engaged opposite to the boost cover with an impeller rotatably engaged between the boost cover and main pump housing. The impeller includes an inducer section comprising a hub including a plurality of axial blades extended therefrom, each of the plurality of blades including a root, a tip, first and second surfaces, wherein the each of the first and second surfaces is defined in TABLE 1. The impeller includes an impeller section comprising a shroud extending from the hub including a plurality of radial blades extended therefrom. Each of the plurality of blades can include including a root, a tip, and opposed pressure and suction sides extending from the root to the tip, wherein the each of the pressure and suction sides is a surface defined in at least one of TABLES 2-4.

Impellers for engine mounted boost stage pumps

An air turbine starter includes a transfer tube having a lubrication inlet and a lubrication outlet configured to allow fluid to flow therethrough. A valve is positioned within the transfer tube including a spring. The spring is configured to selectively allow fluid flow within the transfer tube based on fluid pressure differential across the valve. The spring can have three positions: a first position configured to prevent flow within the transfer tube, an intermediate position configured to allow free flow of fluid within the transfer tube, and a compressed positioned to prevent flow to the lubrication outlet.

Growing community of inventors

DeKalb, IL, United States of America

Benjamin T Harder