Honeywell International Inc.

Alliedsignal Inc.

William J Howe

Mark C Morris

Douglas P Freiberg

Harry Lester Kington

Ardeshir Riahi

Rodolphe Dudebout

Donald L Palmer

Alan Tiltman

George E Zurmehly

Adrian R Allan

James Neumann

Nnawuihe A Okpara

George W Wolfmeyer

Craig W McKeever

Jeffrey E May

Kuo-San Ho

John F Sciacca

Peter L Morgan

Richard J Musiol

Carl D Wright

Alan G Tiltman

Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions. The outer disk portion is bonded to the inner disk portion of the bore section, and the second plurality of blade portions is bonded to the first plurality of blade portions of the bore section.

Compressor impellers, compressor sections including the compressor impellers, and methods of manufacturing

A cooled shroud assembly includes an angled slot and a plurality of dilution jet openings. The shroud forward cavity is modified such that at least one recirculation zone is produced. The angled slot forces an axial change in momentum of the hot gas flow and increases radial and axial pressure variation attenuation. The cooled shroud assembly isolates the shroud structure and seals from the hot flow path and a cooling flow from the dilution jet openings dilutes the hot gas flow. A series of recirculation zones shields the shroud carrier and high pressure seals from the hot gas flow.

Gas turbine cooled shroud assembly with hot gas ingestion suppression

Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.

Variable turbine cooling flow system

A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.

Combustor hot streak alignment for gas turbine engine

A supplemental air cooling system for use in gas turbine engines to inhibit the ingestion of hot flow path gases into circumferential locations of turbine disk cavities is provided. The supplemental air cooling is provided through a simple set of cooling air holes located on each side of the turbine nozzle airfoil trailing edges, and proximately placed to be below the turbine nozzle structural element flow discouragers. Turbine disk cavity cooling purge air entering the disk cavity through the cooling air holes produces dynamic pressure cooling air jets which force the incoming hot ingestion air to turn circumferentially and go back out in the flow path before it enters the turbine disk cavity. The result is a decrease in hot gas ingestion, a reduction in disk rotor and static structural metal temperatures, a reduction in the amount of required cooling air flow, and enhanced performance of the gas turbine engine by virtue of improved specific fuel consumption.

Gas turbine disk cavity ingestion inhibitor

A hot gas recirculation pocket is provided in a gas turbine engine to capture hot gas ingested from an annular hot gas flow path into an internal cooled engine cavity, and to recirculate the ingested hot gas to the hot gas flow path. The engine includes rows of stator vanes and rotor blades mounted in an axially alternating sequence along the hot gas flow path, wherein the rotor blades are peripherally supported by rotor disks disposed within the cooled engine cavity and coupled to a main engine shaft. The recirculation pocket is defined by a contoured shroud mounted within the cooled engine cavity to form a radially outwardly open toroidal-shaped pocket for capturing and recirculating any hot gas ingested through the space between adjacent rows of stator vanes and rotor blades.

Gas turbine engine with hot gas recirculation pocket

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Chandler, AZ, United States of America

William J Howe