United Technologies Corporation

The Boeing Company

Pratt & Whitney Rocketdyne, Inc.

Aerojet Rocketdyne of De, Inc.

Mark David Horn

Kenneth Michael Sprouse

David R Matthews

Shahram Farhangi

Thomas M Walczuk

Calvin Q Morrison, Jr

Alan V Von Arx

James R Lobitz

Shinjiro Miyata

Andreas C Straub

Scott W Fowser

Glenn L Havskjold

Jon C Wagner

Allan Von Arx

Luis A Rosales

An exhaust system includes a multiple of distribution risers which extend transverse to a plenum, each of the multiple of distribution risers includes at least one downstream directed aperture.

Distributed exhaust system

An engine includes a housing having a single wall, where the wall has a rib and a flange, and the wall provides a primary structure and cooling for the engine. A closeout is attached to an outer surface of the wall, and the closeout and the wall form a cavity. The closeout provides a secondary structure for containing a coolant fluid flow within the cavity. The closeout may be corrugated, and the ribs may be exposed to the cavity.

Structurally efficient cooled engine housing for rotary engines

An oil management system includes an engine housing assembly which defines a first rotor volume and a second rotor volume. An oil cooler assembly arranged between the first rotor volume and the second rotor volume.

Integral oil system

A rotary engine which provides a supplemental phase of compression between a first phase of compression and a second phase of compression.

Rotary engine with exhaust gas supplemental compounding

An ignition system for a combustor includes a resonance system which generates an oscillation pressure force by a resonant flow interaction between two parallel interconnected flow passages which carry an incompressible flow. A piezoelectric system driven by said resonance system. An igniter powered by said piezoelectric system.

Piezo-resonance igniter and ignition method for propellant liquid rocket engine

A formed sheet heat exchanger is provided for exchanging heat between fluids is provided. The apparatus includes flow divider sheets that are positioned in a stacked configuration and extend in a longitudinal direction so that adjacent pairs of the sheets define flow passages therebetween for receiving first and second fluids. Each of the sheets is nonuniform in the longitudinal direction, having a manifold portion and a corrugated portion. The corrugated portions of each adjacent pair of sheets define a plurality of fluid channels therebetween that are connected to the portion of the flow passage defined between the manifold portions. The fluid channels are configured to receive the first or second fluids and transfer thermal energy therebetween through the flow divider sheets.

Formed sheet heat exchanger

An ignition system for a rocket engine utilizes the pressure energy in a propellant flow. The propellant flow generates an oscillating pressure force in a resonance system which is then transmitted to a piezoelectric system. The electrical pulses are utilized to generate a spark in an igniter system spark gap, resulting in ignition. Since the spark energy production is driven by the resonance of the propellant flow, a fully passive auto-ignition system is provided. Once ignition occurs, the resultant backpressure in the combustion chamber 'detunes' the resonance phenomena and spark production stops. Furthermore, should the engine flame out, spark production would automatically resume as the propellant valves remain open thereby providing relight capability.

An air/fuel pre-mixer for a gas turbine combustor and a method of pre-mixing air and fuel for a combustor are provided. In one embodiment the pre-mixer includes a first annular premix fuel manifold disposed upstream of the combustor and an annular member concentric with the first premix fuel manifold. Together the annular premix fuel manifold and the annular member define a first venturi shaped air/fuel pre-mix volume between them that has a throat. At or upstream from the throat, the first premix fuel manifold has a plurality of pores whereby the fuel is injected from the first premix fuel manifold to mix with air in the first pre-mix volume. In another embodiment, the annular member is an outer wall, whereas in yet another embodiment, the annular member is a second premix fuel manifold.

Non-swirl dry low NOx (DLN) combustor

A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.

Method and apparatus for a substantially coaxial injector element

The present embodiment relates to a catalytic combustor for reducing the pollutant emissions of combustion. The catalytic combustor described herein employs a novel heat exchange system for rapidly and economically bringing the combustor to a temperature wherein catalytic combustion may occur with minimal production of toxic products.

Cascade ignition of catalytic combustors

The present invention is directed toward a coolant system and method for fabricating a coolant system for actively cooling high performance components utilizing a plurality of feed channels that receive coolant from a manifold through coolant feed tubes and supply coolant to a liner that contains a plurality of coolant channels, each feed channel intersecting and distributing coolant to multiple coolant channels, wherein each coolant channel receives coolant from multiple feed channels.

System and fabrication method for actively cooling high performance components

A method for forming an article having a wall that is at least partially fabricated from tubing. The methodology employs a pressurized fluid to deform the tubing such that an outer surface of the tubing substantially conforms to a predetermined first wall configuration, an inner surface of the tubing substantially conforms to a predetermined second wall configuration and each of segment or loop of the tubing is substantially contiguous with at least one other segment or loop between the first and second surfaces.

Method for forming a tube-walled article

A cooled turbine blade (either a rotor blade or a stationary vane) comprises a blade structural member whose primary function is to withstand the various loads exerted on the blade and maintain structural integrity of the blade, and a heat-transfer sheath that surrounds the outer surface of the structural member. A plurality of coolant passages are formed between the structural member and the heat-transfer sheath. Thus, when coolant is passed through the coolant passages, the heat transferred to the sheath from the hot gases passing through the turbine is in turn transferred to the coolant, which is then removed from the blade, thereby cooling the blade.

Growing community of inventors

Granada Hills, CA, United States of America

Mark David Horn