Hamilton Sundstrand Corporation

Goodrich Corporation

United Technologies Corporation

Otis Elevator Company

Raytheon Technologies Corporation

Rtx Corporation

Rohr, Inc.

Sabic Innovative Plastics IP B.v.

Carrier Corporation

Sabic Global Technologies B.v.

Kidde Technologies Incorporated

Utc Fire and Security Corporation

Georgios S Zafiris

Mark R Jaworowski

Mark R Gurvich

Weilong Zhang

Michael A Kryzman

Zhongfen Ding

Blair A Smith

Joyel M Schaefer

Weina Li

Brayton Reed

Michael King

Bart Antonie Van Hassel

Roque Panza-Giosa

Marilea Manzini

Susanne Marie Opalka

Joseph J Sangiovanni

Zhongfen (Vivian) Ding

Scott Alan Eastman

Rony Giovanni Ganis

Catalin G Fotache

Jeffrey A Anderson

George Hoehn

Brad Guilani

Jose S Alonso-Miralles

Sean C Emerson

Paul Papas

Milan Mitrovic

Promila Bhaatia

Timothy Olson

Terry Muy

Haralambos Cordatos

Vijay V Pujar

Daniel A Mosher

Darin S Lussier

Mark W Costa

John Harner

Tianli Zhu

Bart Antoine Van Hassel

Raymond P Martina

Scott A Smith

Michael T Roland

Martin J Lindway

Imad Hanhan

Kerry E Muenchow

Robert Russell Gallucci

Parmesh Verma

Zissis A Dardas

John P Wesson

Om Prakash

Lei Chen

Steven A Poteet

Jonathan Rheaume

Jean Yamanis

Hua Wang

Hongyi Zhou

Michael A Stark

Mark Alan Sanner

Rajiv Ranjan

Joseph Anthony Suriano

Zhiwei Yang

Yinshan Feng

Gopal R Krishnan

Steven M Kestler

Vicki Herzl Watkins

Bryce Tyler Kelford

Treese Hugener-Campbell

Michael Raymond LaFavor

Theresa Hugener-Campbell

Robert R Hebert

Michael Shoen Davis

Kevin Thomas Gryk

Olivier Brucelle

Himanshu Asthana

Chetan Jayantilal Parikh

Michael Raymond Lafavor

M Shoen Davis

Hari K Harikumar

Aniruddha Moitra

Robert A Schiff

Robert W Walker

Edward P Marron

Mark A Brege

Shaahin Amini

Anais Espinal

Mark R Jaworoski

Marilca Manzini

Martin Lindway

A method for preparing an abradable panel for a rub strip of a fan case of a gas turbine engine includes forming an abradable material into a plurality of panels each comprising an abradable structure; curing the abradable material in the plurality of panels; and installing the plurality of panels into the fan case. The panels can be cured and assembled into a fully assembled rubstrip, and then the assembled rubstrip can be installed into the fan case.

Abradable material and design for jet engine applications

Disclosed is a phosphate coating, comprising: a phosphate portion, wherein the phosphate portion comprises pores, wherein the pores are at least partially filled with a corrosion inhibition sealant, wherein the corrosion inhibition sealant comprises: a base, wherein the base comprises a matrix and a metal within the matrix, wherein the metal within the matrix comprises aluminum, an aluminum alloy, zinc, a zinc alloy, magnesium, a magnesium alloy, or a combination thereof and an inhibitor mixed within the base, wherein the inhibitor comprises zinc molybdate, magnesium metasilicate, trivalent chromium, tungstenate, a metal phosphate silicate, or a combination thereof.

Phosphate coating which can be substantially free of hexavalent chromium and methods of making the same

In accordance with at least one aspect of this disclosure, a composite structure can be formed of or including a plurality of composite strips. The plurality of composite strips include one or more filler strips which can have at least one filler edge having a filler edge geometry between a first surface and second surface, the second surface being opposite the first surface. The filler edge geometry can be configured to prevent formation of one or more gaps between one or more adjacent composite strips.

Composite structures

A drive shaft has a tubular portion extending between axial ends and is hollow. There are deformations on the tubular portions. The deformations extend for a circumferential extent that is less than 180° about a central axis of the tubular portion.

Drive shafts with enhanced bending flexibility

A drive shaft for transferring torque including a tubular insert extending along an axis and defining a first layer of the drive shaft including at least one straight portion and at least one undulation, wherein the tubular insert includes a first material having a first deformation temperature, and a polymeric tubular covering defining a second layer of the drive shaft surrounding the tubular insert including a second material having a deformation temperature lower than the deformation temperature of the first material, wherein the covering includes at least one straight portion adjacent to the straight portion of the tubular insert and at least one undulation adjacent to the at least one undulation of the tubular insert.

Hybrid composite drive shaft and a method of making

A gas turbine engine component includes a metal substrate and a coating system disposed on the metal substrate. The coating system includes at least one layer of aluminum-chromium oxide.

Aluminum-chromium oxide coating and method therefor

A drive shaft for an aircraft according to an example of the present disclosure includes, among other things, an elongated core extending between a pair of opposed couplings, an energy absorption layer made of a composite comprising metal, the energy absorption layer disposed on the core, and a first composite ballistic layer disposed along a length of the core.

Ballistic resistant drive shaft

A sealing process includes applying a first reactant to a substrate having a porous structure, the first reactant comprising a chromium (III) precursor and a transition metal precursor and applying a second reactant to the first reactant, the second reactant comprising a rare earth element precursor and an alkaline earth element precursor to form reservoirs of trivalent chromium in pore space of the porous structure, and a physical barrier over the substrate and the reservoirs.

Sealing process for an anodized aluminum-alloy surface

A method is disclosed for treating an anodized metal surface. According to the method, polynuclear clusters comprising aluminum oxide hydroxide are applied to the anodized metal surface.

Treated anodized metal article and method of making

An abradable material for a rub strip of a gas turbine engine component includes a polymer matrix, and an organic or inorganic filler distributed through the matrix, wherein the abradable material has a compression spring rate profile including: less than 50,000 lb/in at −65° F., less than 35,000 lb/in at room temperature, and less than 35,000 lb/in at 200° F.

A polymer-matrix fiber-reinforced composite structure includes a plurality of polymer composite layers having at least one polymer composite layer that includes a first polymer-matrix and a first fluorescent agent interspersed through the first polymer-matrix. Damage to the polymer composite structure results in a change in fluorescence at the point of damage. A method for detecting damage in the polymer composite structure described above including the steps of applying light having a wavelength selected to induce fluorescence in the first fluorescent agent to the polymer composite structure, detecting a detected fluorescence pattern, and comparing the detected fluorescence pattern to a predetermined normal fluorescence pattern.

Composite structures with damage detection capability

A composite/metal joint includes a composite member, a metallic member, a cylindrical liner, and a fastener. The composite member has a first aperture. The metallic member is disposed adjacent to the composite member and has a second aperture coaxially aligned with the first aperture. The cylindrical liner extends longitudinally from a first end to a second end. The cylindrical liner has a cylindrical outer liner surface and a longitudinally extending third aperture coaxial with the first and second apertures and defined by an inner liner surface. The cylindrical liner is disposed in the first and second apertures with the outer liner surface adjacent to aperture walls of the first and second apertures. The cylindrical liner has a plurality of grooves intersecting the outer liner surface. The fastener is disposed through the third aperture of the cylindrical liner and is configured to attach the metallic member to the composite member. An outer surface of the fastener is in direct contact with the inner liner surface.

Composite/metal joints

A method of applying a trivalent chromium or chromium-free conversion coating to a metallic substrate including mixing a dye compound that interacts with electromagnetic radiation outside the human visual spectrum but not electromagnetic radiation that is within the human visual spectrum to produce an observable emission into the trivalent chromium or chromium-free conversion coating mixture to allow for inspection of the coating after applied with a correlating electromagnetic radiation source.

Additive for quality determination of conversion coatings

A composite shaft includes a shaft body formed from a plurality of polymer impregnated fiber-reinforced material layers having an annular outer surface and an annular inner surface defining a passage. A plurality of internal support members extend along the passage. Each of the plurality of internal support members includes a support body formed from molded plastic having an outer surface that abuts the annular inner surface of the support body, a first end, an opposing second end, and a circular end wall arranged at one of the first end and the opposing second end.

Buckling resistant composite shaft and method of making a buckling resistant composite shaft

Growing community of inventors

Glastonbury, CT, United States of America

Georgios S Zafiris