United Technologies Corporation

Hamilton Sundstrand Corporation

Raytheon Technologies Corporation

Takao Fukuda

Francis R Price

James Preston Downs

Edward F Pietraszkiewicz

Joel H Wagner

Scott W Simpson

Eric A Grover

Shankar S Magge

David J Zawilinski

Richard W Hoff

Ky H Vu

Lisa P O'Neill

Andrew P Boursy

Irwin D Singer

Daniel C Nadeau

Robert L Hazzard

Ryan Shepard Levy

Norman F Roeloffs

Andy Turko

Conan P Cook

David Michael Kontrovitz

Steven G Lemieux

Lynn M Boy

Gerald M Mace

Scott D Hartmann

Paul Smith

Edward M Henrahan

Brenda Zhang

Lnyy M Boy

Gerald M Mace Jr

Normal F Roeloffs

A system includes an air turbine starter having an inlet, a turbine air exhaust outlet, an output shaft, and a turbine in fluid communication with the inlet and the turbine air exhaust outlet. The turbine is operably coupled to the output shaft. The system also includes an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet.

Air turbine starter with turbine air exhaust outlet valve

An airfoil cluster includes an inner diameter platform and an outer diameter platform. A plurality of airfoils extend radially from the inner diameter platform to the outer diameter platform. Each airfoil has a leading edge and a trailing edge, and pressure and suction sides between the leading and trailing edges. At least one of the airfoils includes a recessed portion on the pressure side adjacent to the trailing edge.

Airfoils

An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Gas turbine engine airfoil platform edge geometry

A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine.

Retrofit dirt separator for gas turbine engine

A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge. The trailing edge region includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.

Turbine blade trailing edge construction

Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.

Airfoil profile with optimized aerodynamic shape

A coolable airfoil having a passage for discharging particulates entrained in cooling air is disclosed. Various construction details are developed to provide clean cooling air to the leading edge of the airfoil. In one embodiment, a chordwise duct extends past a spanwisely extending supply passage to the inlet of a spanwisely extending rear passage such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage and into the rear passage and a larger portion of the flow of cooling air into the supply passage for cooling the leading edge of the airfoil.

Coolable airfoil

Growing community of inventors

East Hartford, CT, United States of America

Takao Fukuda