General Electric Company

Walter Jackson Tingle

John Alan Manteiga

Stephen John Howell

Kevin Richard Kirtley

John Carl Jacobson

Timothy Patrick McCaffrey

William Steyer

Barry Francis Barnes

Timothy Joseph Higgins

Christopher Marlow Kieffer

Wayne R Oliver

John Paul Petrowicz

Timothy A White

Kevin F Canillas

Timothy P Mccaffrey

A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.

Segmented inertial particle separators and methods of assembling turbine engines

A particle separator which broadly includes: an inner wall, an outer wall and a splitter, wherein the inner and outer walls define an air intake passageway, and wherein the splitter is positioned between the inner and outer walls so as to define a scavenge air flow passageway connected to the intake passageway and a main air flow passageway connected to the intake passageway; the inner wall having a humped-shaped portion between the intake passageway and the main air flow passageway; the humped-shaped portion having a peak and a radius of curvature at any point on the hump-shaped portion of the inner wall after the peak corresponding to a degree of curvature of from about 30 to about 60 degrees; and a boundary layer control mechanism for providing active boundary layer control along the inner wall after the peak and within the main air flow passageway. Also provided is a method for providing active boundary layer flow control along the inner wall after the peak and within the main air flow passageway.

Particle separator using boundary layer control

A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Infrared suppressor apparatus and method

A method enables a gas turbine engine to be assembled. The method includes providing a combustor including a liner that defines a combustion chamber therein, and coupling a casing within the gas turbine engine to extend circumferentially around the combustor liner, wherein the casing includes an inlet and a scroll duct that is coupled in flow communication to the inlet and extends at least partially circumferentially around the liner. The method also includes coupling the inlet in flow communication with a feed air source.

Methods and apparatus for supplying feed air to turbine combustors

A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a fuel injector including a fuel inlet and an air inlet to the combustor casing such that the fuel injector extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor, and coupling the air inlet to an air source such that cooling air received therethrough is circulated through the fuel injector to facilitate cooling the fuel injector.

Methods and apparatus for operating gas turbine engine combustors

A fuel injector includes outer and inner coaxial shells spaced radially apart to define a flow channel therebetween having an inlet and an outlet. A strut extends radially outwardly from the inner and outer shells at leading edges thereof and is fixedly joined thereto. An annular lobed mixer is disposed coaxially in the channel and includes a leading edge, a trailing edge spaced from the channel outlet to define a mixing nozzle, and a plurality of circumferentially spaced apart lobes increasing in radial height from the leading to trailing edges of the mixer. The lobes defines with the outer and inner shells corresponding pluralities of outer and inner chutes for separately channeling respective portions of inlet air. The fuel is injected into the lobed mixer forming a fuel and air mixture in the mixing nozzle for discharge through the channel outlet into a combustor.

Low NO.sub.x lobed mixer fuel injector

Laminar flow tubes of uniform inner diameter and length are individually incorporated in each of plural fuel lines leading from a distributor to the various fuel injectors in a gas turbine combustor to provide generally uniform fuel distribution over a wide range of fuel flow rates, thus eliminating the need for a variable fuel metering valve in each fuel line.

Growing community of inventors

Danvers, MA, United States of America

Walter Jackson Tingle