General Electric Company

Ge Avio S.r.l.

Douglas Downey Turner

Arthur William Sibbach

Daniel Alan Niergarth

Valeria Proano Cadena

Michael Macrorie

Vincenzo Martina

Jorge De Luis

Keith W Wilkinson

Marco Venturato

Gregory Allen Boardman

William Thomas Bennett

Steven C Steffens

Brian Michael Royer

A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (A) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (A) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (T) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: wherein CSP is greater than 0.0001194×EGT−0.103×EGT+22.14 and less than 0.0003294×EGT−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Gas turbine engine

The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.

Fuel nozzle assembly with impingement purge

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner that at least partially define a combustion chamber. The annular dome defines a plurality of circumferentially spaced fuel injection ports and a plurality of mounting assemblies are configured for receiving and supporting a plurality of fuel injector assemblies within the fuel injection ports. Each mounting assembly includes a ferrule positioned adjacent to and extending around a peripheral edge of the respective fuel injection port. A spring finger is coupled to an interior surface of the ferrule and extends toward a centerline of the fuel injection port to form a seal with the fuel injector assembly.

Combustor mounting assembly having a spring finger for forming a seal with a fuel injector assembly

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West Chester, OH, United States of America

Douglas Downey Turner