Honeywell International Inc.

Ly D Nguyen

Stony Kujala

Gregory O Woodcock

Cristopher Frost

Jason Smoke

Louis D Cruse

Lori Wheeler

Richard D Kocher

Ivar Gene Fowkes

Silvestre Salas

William North

Vadanth Kadambi

James Lolnell Hadder

George E Zurmehly

Jeff Guymon

Ronald P Maty

Greg Ockenfels

Darrell K James

Gary A Shoff

Hakan Aksoy

John M Wait

An integrated assembly is provided for a centrifugal compressor, which integrates selected static portions of the centrifugal compressor into a monolithic structure to allow a small deflection of the inner flow path at assembly. The integrated assembly may include a machined compressor shroud casting having integral diffuser vanes, an aft sheet metal inner flow ring having a radially extending rim with slots in the inner flow ring for receiving diffuser vanes and slots in the rim for receiving deswirler vanes, an outer deswirler band surrounding the inner flow ring and having slots opposing those in the rim, and a plurality of deswirler vanes for fabrication between the inner flow ring and the deswirler band within the respective slots.

Integral diffuser and deswirler with continuous flow path deflected at assembly

A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.

Turbomachine compressor scroll with load-carrying inlet vanes

A gas turbine engine comprises a turbine scroll inside a combustor housing, discouragers with 90-degree bending angles, a radial nozzle contacting a forward bayonet on the forward side of the turbine scroll at a bayonet engagement point and a B-width measured between the discouragers. Retaining ring maintains the size of the B-width. The turbine scroll may have eight surfaces sealing at four locations and a provision to maintain constant 'B-width' for the thin sheet metal scroll within the combustion system. The design allows the scroll to operate at high temperature while maintaining lowest possible thermal and mechanical stresses. It can be easily assembled with excellent capability to control gas leakage and minimal component interface wearing or fretting. The gas turbine engine is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially high performance, high cycle flight vehicles.

Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine

An integral assembly that may improve control over thermal and mechanical behaviors of assembly structures during various transient operation conditions is disclosed. The integral assembly comprises a continuous ring disposed coaxial with, and orthogonal to a central axis, the continuous ring comprising a plurality of surfaces, the plurality of surfaces having a continuous outer surface and a continuous inner surface; the plurality of surfaces being characterized by a continuous cross section having a first cross sectional dimension longitudinally disposed parallel to the central axis; the plurality of surfaces comprising a bell mouth surface in physical communication with a compressor shroud surface; the compressor shroud surface being in physical communication with a diffuser surface; and the diffuser surface being in physical communication with the bell mouth surface. The integral assembly comprising a compressor shroud is also provided. An auxiliary power unit including the integral assembly, and a method of making the integral assembly are also disclosed.

Performance and durability improvement in compressor structure design

A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.

Conical helical of spiral combustor scroll device in gas turbine engine

A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.

Multi-axial pivoting combustor liner in gas turbine engine

A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.

Integral compressor housing of gas turbine engines

A turbine scroll retention ring may comprise a retainer ring, a plurality of ring fingers, and a plurality of ring joggles. The turbine scroll retention ring may surround and be attached to a radial nozzle. The ring joggles may allow for thermal growth variations between the radial nozzle and the turbine scroll retention ring. The radially outer end portions of the ring fingers may be in contact with a turbine scroll component (for example, an aft scroll ring), such that the turbine scroll retention ring may force contact between the turbine scroll component and the radial nozzle. The finger joggles of the ring fingers may allow for thermal growth variations between the radial nozzle and the turbine scroll component. The turbine scroll retention ring may provide constant axial loading to the aft scroll ring during all engine operating conditions.

Thermally stabilized turbine scroll retention ring for uniform loading application

A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.

Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine

A method for forming a thermally isolating gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is positioned within the turbine housing with an outer baffle arranged about the floating liner and an inner baffle arranged within the floating liner. The inner and outer baffles are welled or brazed to the floating liner assembly to form a unitary assembly creating a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

Method of forming a thermally isolated gas turbine engine housing

An apparatus and system for thermally isolating a gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is assembled within the housing with an outer baffle surrounding the floating liner and an inner baffle disposed within the floating liner. The floating liner creates a thermally isolated device to cover and protect the housing from high temperature. Openings formed in the outer baffle, floating liner and inner baffle create a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

Growing community of inventors

Phoenix, AZ, United States of America

Ly D Nguyen