General Electric Company

General Electric Company Polska Sp. Z O.o.

Ge Marmara Technology Center Muhendislik Hizmetleri Ltd

Nicholas Joseph Kray

Nitesh Jain

Arthur William Sibbach

Abhijeet Jayshingrao Yadav

David William Crall

Ravindra Shankar Ganiger

Daniel Edward Mollmann

Scott Roger Finn

Gary Willard Bryant, Jr

Elzbieta Kryj-Kos

Gregory Carl Gemeinhardt

Li Zheng

Peggy Lynn Baehmann

Douglas Duane Ward

Stefaan Guido Van Nieuwenhove

Tod Winton Davis

Viswanadha Gupta Sakala

Dong-Jin Shim

Brandon Wayne Miller

Kishore Budumuru

Nagamohan Govinahalli Prabhakar

Narendra Digamber Joshi

Apostolos Pavlos Karafillis

Changjie Sun

Manoj Kumar Jain

Ian Francis Prentice

Todd Alan Anderson

Michael John Franks

Yanyan Wu

Kirti Arvind Petkar

Qiang Li

Mark Ernest Vermilyea

Trevor Howard Wood

Praveen Sharma

Max Robert Farson

Aaron Todd Sellinger

Andrew Breeze-Stringfellow

Ming Xie

Wendy Wenling Lin

Suresh Subramanian

Francis Howard Little

Andrew J Lammas

Gerald Alexander Pauley

Ambika Shivamurthy

Bin Wei

Jan Christopher Schilling

Kishore Ramakrishnan

Thomas James Batzinger

James Thompson

Andrew Lee Trimmer

Frank Worthoff

Joshua L Miller

Egbert Geertsema

Donald Lee Gardner

Michael Scott Lamphere

Shatil Sinha

Jian Ying Li

Michael Harvey Schneider

Howard Paul Weaver

Leslie L Langenbrunner

Benjamin James Roby

Thomas Ory Moniz

Bugra Han Ertas

Jeffrey Donald Clements

Bhaskar Nanda Mondal

Hiranya Kumar Nath

Scott Alan Schimmels

Waseem Ibrahim Faidi

Prabhjot Singh

Vidyashankar Ramasastry Buravalla

Michael Edward Eriksen

Edward James Nieters

Erich Alois Krammer

Changting Wang

Giridhar Jothiprasad

James Norman Barshinger

Veeraraju Vanapalli

Shridhar Champaknath Nath

Arun Kumar

Dean Michael Robinson

Nicholas M Daggett

Bowden Kirkpatrick

Sesha Subramanian

Sultan Shair

Shivam Mittal

Joel Francis Kirk

Pinghai Yang

Ram Kumar Upadhyay

Thomas Malkus

Naleen Kumar Verma

Ruben Egberto Fairman

Kevin Lee Kirkeng

Shawn Patrick Riley

Xiaomei Fang

Haiyan Sun

Deepak Ghiya

Bhujabal Prashant Mahadeo

Paul Izon

Ming Cheng Li

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having 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; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (Fn) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: Fn×EGT/(A×1000).

Gas turbine engine

A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

Pitch change mechanism for a fan of a gas turbine engine

A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.

Rotor assembly for a gas turbine engine

A turbine engine experiences 1P vibrations. The turbine engine includes a turbo-engine, a compressor for compressing air, and a combustor for combusting fuel and the compressed air to generate combustion gases. A turbine receives the combustion gases and drives a fan assembly. The fan assembly includes a fan disk and a fan blade with a fan blade centerline axis. The fan blade is subjected to 1P loading, generating the 1P vibrations. A fan blade root fixed to the fan blade and connected to the fan disk, is aligned with the fan blade centerline axis, and conducts the 1P vibrations. A damper positioned radially between the fan blade root and the fan disk damps the 1P vibrations.

Turbine engine including a fan assembly having a damper

A turbine engine for an aircraft. The turbine engine includes a vane support and a vane. The vane support has a vane-facing surface. A first hook and a second hook extend from the vane-facing surface and define a channel therebetween. The vane includes an airfoil and an outer band connected to the airfoil. The outer band is positioned in the channel to form a gap between a support-facing surface of the outer band and the vane-facing surface under assembly conditions of the turbine engine. The vane-facing surface and the support-facing surface are shaped to form a contact configuration that occurs when, under an operating condition of the turbine engine, the vane flexes and at least a portion of the support-facing surface contacts the vane-facing surface over a contacting region to eliminate the gap over the contacting region.

Turbine engine including a vane support and a vane

An airfoil assembly for a turbine engine, the airfoil assembly including a platform defining an inner surface and an outer surface, a variable pitch airfoil extending radially from the outer surface of the platform from a root to a tip to define a span length and a mounting structure connected to the platform.

Variable pitch airfoil

A turbine engine comprising a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement and defining a stator portion and a rotor portion, which rotates about an engine centerline. The rotor portion comprising a variable pitch airfoil assembly. The variable pitch airfoil assembly having an airfoil and a balancing insert.

Turbine engine having a variable pitch airfoil assembly

Outlet guide vane mounts with an airfoil structure are disclosed herein. The airfoil structure includes an airfoil platform, a composite material, a load spreader block, and a shim material, the composite material and a load spreader block positioned on the airfoil platform, the composite material having a first stiffness and the load spreader block having a second stiffness, and a shim material positioned between the composite material and the load spreader block, the shim material having a third stiffness different from at least one of the first stiffness or the second stiffness.

Outlet guide vane mount

A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Turbine engine with composite airfoils

A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.

Collars to retain multiple fan blades for use with an aircraft engine are disclosed herein. An example gas turbine engine includes a plurality of fan blades and a collar coupled to the plurality of fan blades. The collar includes a first mating piece and a second mating piece coupled to the first mating piece. The first and second mating pieces define an opening configured to receive a first root of a first fan blade of the plurality of fan blades, and the first and second mating pieces define a slot to retain a second root of a second fan blade of the plurality of fan blades.

Pitch-controlled blade retention collar

A composite airfoil assembly has a composite airfoil, a spar, and a wrap. The composite airfoil has an outer wall and a composite skin. The outer wall extends between a root and a tip. The outer wall defines an interior. The composite skin at least partially defines the outer wall. The spar having a spar centerline axis, a stem, a base, and a transition interconnecting the base and the stem.

Composite airfoil assembly having a composite airfoil and spar

A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.

Turbine engine airfoil with a woven core

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.

Composite airfoil assembly for a turbine engine

A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.

Turbine engine with a primary stage of airfoils and a subsidiary stage of airfoils

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Mason, OH, United States of America

Nicholas Joseph Kray