Raytheon Technologies Corporation

United Technologies Corporation

Hamilton Sundstrand Corporation

Jesus A Garcia

Evan J Butcher

Lawrence A Binek

Jesse R Boyer

Faramarz Zarandi

Michael Winter

Loc Quang Duong

Sean R Jackson

Xiaolan Hu

Gao Yang

Dan G Sapiro

Matthew B Kennedy

Benjamin E Fishler

Gregory G Johnson

Nagendra Narasimha Kedlaya

Ralph E Gordon

Phillip Creed

Jesse R Boy

Steven R Falconer

Ulrike Kaul

Sean G Breadmore

Rene Remon

Emmanuel Medel

Disclosed is a method of making a part, comprising: forming the part via an additive manufacturing process, wherein the additive manufacturing process comprises layering, melting, and solidifying a metal alloy based on a three dimensional numerical model, wherein the formed part comprises a microstructure, wherein the microstructure comprises an average columnar grain length; and heat treating the formed part, wherein heat treating comprises heating to between 750° C. and 1200° C. for a time between 0.5 hours and 10 hours and then cooling the formed part below 750° C., wherein after heat treating, the formed part has an average columnar grain length of about 400 micrometers to about 1000 micrometers, as measured using electron backscattered diffraction.

Method of making a radial turbine wheel using additive manufacturing

Gun sight

A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

Attritable engine additively manufactured inlet cap

A double walled stator housing includes a first stator housing wall, a second stator housing wall located radially outward from the first stator housing wall, and an air gap located between the first and the second stator housing walls. The housing also includes at least one support structure attached to the first stator housing wall and the second stator housing wall, spanning the air gap and configured to minimize heat transfer between the first wall and the second wall.

Double walled stator housing

A method of making a rotor assembly of a turbojet includes building the rotor assembly via layer-by-layer additive manufacturing. A turbine portion is formed and a compressor portion is integrally formed with the turbine portion. A shaft portion is integrally formed with the compressor portion. A material of the rotor assembly includes a nickel based alloy.

Unitized rotor assembly

A containment structure for a gas turbine engine includes a stator shroud with a wall. The stator shroud wall extends axially between a shroud inlet aperture and the shroud outlet aperture. The wall includes a stainless steel alloy material having less than 44% nickel by mass to provide containment protection for an impeller rotateably disposed within an interior of the stator shroud.

Gas turbine engine containment structures

A rotor blade comprises a blade platform and an airfoil. The airfoil comprises a blade tip, a leading edge, and a trailing edge with a stiffening compound lean contour. The blade tip is radially opposite the blade platform, and defines a blade span between the blade itself and the blade platform. The leading and trailing edges extend from the blade platform to the blade tip to define blade chords between the leading edge and the trailing edge. The compound lean contour comprises a positive lean section located at the lean tip, and extending along a lean axis to a lean end. The negative lean section is located radially inward of the positive lean section, and extends along the lean axis to the lean end.

Detuning trailing edge compound lean contour

A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.

Reduction of equally spaced turbine nozzle vane excitation

Panic alert transmitter

Growing community of inventors

San Diego, CA, United States of America

Jesus A Garcia