Hamilton Sundstrand Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Otis Elevator Company

Delavan Inc.

Vijay Narayan Jagdale

Lawrence A Binek

Jesse R Boyer

Evan J Butcher

Om Parkash Sharma

Dmytro Mykolayovych Voytovych

Matthew B Kennedy

Ranadip Acharya

Bryan Galbraith Dods

Tahany Ibrahim El-Wardany

John A Sharon

Colette Opsahl Fennessy

Thomas M Yun

Sergey Mironets

Wayde R Schmidt

Paul Sheedy

James Thompson Beals

Ying She

Brian St Rock

John P Wesson

Sergei F Burlatsky

William A Veronesi

Jagadeesh Kumar Tangudu

David Ulrich Furrer

Alexander Staroselsky

Sameh Dardona

Brad Guilani

Diana Giulietti

Gopal R Krishnan

Tommy Skiba

Matthew E Lynch

Jun Ma

Kiley James Versluys

Yanzhi Chen

David R Polak

Peter Keyo

David J Lanesey

Changle Li

Loren O Brandenburg

Qingqing Zhang

Abhay Taneja

Alexander Bosworth

Sladjan Lazarevic

Jin Lee

A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Additively controlled surface roughness for designed performance

A computer-implemented method for additive manufacturing can include receiving, by one or more computing devices, three-dimensional model data, and receiving, by the one or more computing devices, one or more inducing variables. The one or more inducing variables can include at least one of a recoater direction, recoater force, gas flow direction, and/or gas flow rate. The computer-implemented method can also comprise creating a print file as a function of the one or more inducing variables to account for the inducing variables to produce a uniform part throughout a build area or otherwise reduce part variability and outputting the print file to a printer or a data storage device.

Accounting for inducing variables in additive manufacturing

A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

Kinetic disassembly of support structure system for additively manufactured rotating components

A heat exchanger arrangement includes walls defining at least two circuit passages for porting a first fluid, a first of the circuit passages defining a first passage length, and a second of the circuit passages defining a second passage length, the second passage length being different from the first passage length, the walls being in thermal communication with a second fluid while isolating the first fluid from the second fluid, at least one of the first circuit passage and the second circuit passage includes a flow control feature configured to decrease an imbalance in flow between the first circuit passage and the second circuit passage compared to if the flow control feature were not present.

Conformal heat exchanger passage features for improved flow distribution

A process for additive manufacturing of a metal alloy material is provided that includes: a) providing a feedstock powder comprising base powder particles with nanoparticles attached to surfaces of the base powder particles; b) providing an additive manufacturing system with a laser power source relatively movable at a scan speed; c) wherein the additive manufacturing system has a process window for the feedstock powder; and d) exposing the feedstock powder to a predetermined power input from the laser power source at a predetermined scan speed to produce the metal alloy material. The concentration by volume of nanoparticles within the feedstock powder is such that independent first and second microstructures may be produced within the metal alloy material.

Method for additive manufacturing with modified powder

A method of additively manufacturing includes generating a thermal model driven scan map that identifies an equiaxed cap region, a single crystal (SX) region, and a columnar to equiaxed transition (CET) region; and forming an active melt pool with respect to the thermal model driven scan map such that a depth of the active melt pool is greater than a thickness of the equiaxed transition (CET) region.

Additive manufacturing based multi-layer fabrication/repair

An additively manufactured heat exchanger can include a plurality of vertically built fins, and a plurality of non-horizontally built parting sheets. The plurality of vertically built fins can extend between and connect to the plurality of parting sheets. The heat exchanger can include a plurality of layers of fins and parting sheets. The heat exchanger can include first and second flow circuits for allowing separate fluid flows to flow through the heat exchanger to exchange heat therebetween.

Additively manufactured heat exchangers and methods for making the same

An additively-manufactured heat exchanger includes fluidly-separated alternating first and second layers having respective flow channels which can include one or more features that is either a riblet or a turbulator. A riblet includes a riblet peak and/or a riblet valley, which has a riblet slope, and the riblet peak and/or riblet valley has a riblet axis that is generally parallel to either the first fluid flow direction or the second fluid flow direction. A turbulator includes a turbulator peak and/or a turbulator valley, which has a turbulator slope, and the turbulator peak and/or turbulator valley has a turbulator axis that is generally perpendicular to either the first fluid flow direction or the second fluid flow direction. The respective slope angles are generally 25-65 deg. relative to build-axis, thereby resulting in improved surface roughness and uniformity control during the build process.

Heat exchanger riblet and turbulator features for improved manufacturability and performance

An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.

Additively manufactured thermally insulating structure

An assembly for use in an attritable engine includes a hub and a blade. The hub is configured to rotate about a centerline axis passing through a center of the hub and is formed with a first type of layer-by-layer additive manufacturing process. The blade is connected to and extends radially outward from the hub. The blade is formed with a second type of layer-by-layer additive manufacturing process that is different than the first layer-by-layer additive manufacturing process. The hub and the blade are integrally formed together as a single piece of material with a layer-by-layer additive manufacturing process. The blade includes a root of a first material, a platform connected to the root, an airfoil connected to and extending from the platform, and a tip connected on a distal end of the airfoil opposite from the root. The platform includes a material that is different from the first.

Multi-material rotor for attritable engines

A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.

Attritable engine integrated with vehicle

A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

Gas turbine engine with a unitary structure and method for manufacturing the same

Growing community of inventors

South Windsor, CT, United States of America

Vijay Narayan Jagdale