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US20140140820 AEROENGINE SEALING ARRANGEMENT  
A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential...
US20100316488 MIXING HOTTER STEAM WITH COOLER STEAM FOR INTRODUCTION INTO DOWNSTREAM TURBINE  
Apparatus and methods are presented for mixing a high temperature steam, perhaps leaked from an upstream turbine, with the cooler steam from a lower temperature, downstream turbine and introducing...
US20140169946 EXHAUST-GAS TURBOCHARGER  
An exhaust-gas turbocharger (1) having a turbine (2) which is provided with a variable turbine geometry (18) and/or a wastegate; and having an actuator (11) which is connected to the variable...
US20120099964 TURBOCHARGER TURBINE  
A turbocharger turbine having a double-layer flow passage and a variable cross-section, including a turbine housing, a volute diffuser channel, a power turbine, a volute gas feeding passage, and a...
US20130280046 BYPASS TURBOJET  
A bypass turbojet including a fan wheel carrying blades and surrounded by an annular casing, the casing including an air suction mechanism sucking air from an annular clearance formed between the...
US20130343867 GAS TURBINE ENGINE WITH REVERSE-FLOW CORE HAVING A BYPASS FLOW SPLITTER  
A gas turbine engine includes a bypass flow path. A core flow path has a reverse duct configured to reverse a direction of core flow. The core flow path includes an exhaust duct in fluid...
US20110027072 BYPASS SYSTEM FOR PURGING AIR FROM A SUBMERSIBLE PUMP  
A submersible pump, and method of making the submersible pump, is disclosed. The pump comprises a housing, a plurality of impeller stages serially disposed in the housing from a bottom impeller...
US20150184542 Turbine housing for a turbocharger  
A turbine housing for a turbocharger has a plurality of interconnected housing parts. A central, one-piece contoured component that is constructed as a cast component or a forged component is...
US20140060005 MAGNETIC ADVANCED GENERATION JET ELECTRIC TURBINE  
Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and...
US20150010382 TURBINE FLOW MODULATION FOR PART LOAD PERFORMANCE  
Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser....
US20120171019 ATTACHMENT INTERFACE FOR A GAS TURBINE ENGINE COMPOSITE DUCT STRUCTURE  
A duct includes a first and second composite duct section and a first and second metallic support ring section the second metallic support ring section abuts the first metallic support ring section.
US20140072411 TURBINE WASTEGATE  
An assembly can include a turbine housing that includes a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat; a bushing configured for receipt by the bore; a...
US20140072410 TURBINE WASTEGATE  
An assembly can include a turbine housing that includes a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat; a bushing configured for receipt by the bore; a...
US20150247462 GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM FOR HEAT EXCHANGER USING BYPASS FLOW  
A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a...
US20120207590 ANTI-AIRLOCK PUMP  
A pump having anti-airlock provisions. The pump is comprised of a volute comprised of a volute wall, and an impeller comprising back vanes on a side of the impeller that is proximate to the volute...
US20120128467 INTEGRATED VARIABLE GEOMETRY FLOW RESTRICTOR AND HEAT EXCHANGER  
One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide...
US20150152789 MULTI-BYPASS STREAM GAS TURBINE ENGINE WITH ENLARGED BYPASS FLOW AREA  
A gas turbine engine comprises a first bypass flow path housing configured within the engine, radially exterior to an engine core housing, and a second bypass flow path housing configured within...
US20120243972 GAS TURBINE ENGINE SYSTEMS INVOLVING INTEGRATED FLUID CONDUITS  
Gas turbine engine systems involving integrated fluid conduits are provided. In this regard, a representative engine casing for a gas turbine engine includes: a casing wall; and a fluid conduit...
US20130330175 REHEAT STEAM BYPASS SYSTEM  
Various embodiments include systems for controlling the flow of main steam from a high-pressure (HP) turbine to a turbine packing. In some cases, a system is disclosed including: a high pressure...
US20140013767 BAFFLE ASSEMBLY FOR BLEED AIR SYSTEM OF GAS TURBINE ENGINE  
A baffle assembly for a housing of a combustor system of a gas turbine engine is provided. The baffle assembly includes a baffle retainer and a baffle. The baffle retainer includes a retainer tube...
US20150260051 GEARED LOW FAN PRESSURE RATIO FAN EXIT GUIDE VANE STAGGER ANGLE  
A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The...
US20090175716 Integrated bypass engine structure  
One form of the present invention contemplates an apparatus comprising a gas turbine engine core, a gearbox accessory mounted to the engine core and substantially enclosed by an inner fairing; a...
US20140369804 VARIABLE BLEED SLOT IN CENTRIFUGAL IMPELLER  
The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210,...
US20090007567 Dual Flow Turbine Engine Equipped with a Precooler  
The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in external contact...
US20140072412 TURBINE WASTEGATE  
An assembly can include a turbine housing that includes a bore, a wastegate seat and two wastegate passages that extend to the wastegate seat; a rotatable wastegate shaft configured for receipt by...
US20150167676 Gas Turbine Engine for Long Range Aircraft  
A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a...
US20140062092 UNDERGROUND WATERMILL  
A waste-watermill for generating electrical energy from a flow of waste water running through an underground waste-water conduit. The flow of waste water defines a free surface and a flow...
US20130309070 INNER BYPASS DUCT WALL ATTACHMENT  
A bypass duct of a gas turbine engine has an inner bypass duct wall has a front end portion which is rigidly mounted to an engine core case and a rear end portion which is flexibly mounted to the...
US20130058762 Turbo Compressor  
In order to improve a turbo compressor comprising a compressor housing, in which an incoming gas volume flow is supplied to an impeller channel through an inlet channel, is compressed in the...
US20150204212 HIGH DURABILITY TURBINE EXHAUST CASE  
A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least...
US20150132110 HIGH DURABILITY TURBINE EXHAUST CASE  
A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least...
US20150260127 Aircraft Turbofan Engine with Multiple High-Pressure Core Modules Not Concentric with the Engine Centerline  
An aircraft turbofan engine configuration is described that has two or more high-pressure core modules operating in parallel flowpaths, each comprised of a compressor, a combustor, and a turbine,...
US20050141991 Method for conditioning a compressor airflow and device therefor  
In a method for conditioning a compressor airflow in an axial compressor which comprises in a coaxial arrangement a central rotor and stator surrounding said rotor, an airflow is sucked in at an...
US20080178591 ARRANGEMENT OF A TWO STAGE TURBOCHARGER SYSTEM FOR AN INTERNAL COMBUSTION ENGINE  
Arrangement of a two stage turbocharger system for an internal combustion engine comprising an intake manifold and an exhaust manifold, comprising a low-pressure turbocharger, a high-pressure...
US20080112791 Compound turbine cooled engine  
A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The...
US20110194928 BLOW-OFF SYSTEM FOR MULTI-STAGE TURBO COMPRESSOR  
The present invention relates to a blow-off system for a multi-stage turbo compressor that includes a plurality of blow-off pipes disposed according to respective stages of the multi-stage turbo...
US20070237626 Cooling channel for a fan motor for a ventilation, heating, and/or air conditioning system  
Ventilating device (1) comprising a casing (6) intended to channel at least one air flow (3) created by a blower wheel (5), the said casing (6) delimites a main air channel (7) in which a main air...
US20080112794 Compound nozzle cooled engine  
A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit...
US20120321448 AIRCRAFT POWERPLANT  
A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass...
US20090259379 REDUCED TAKE-OFF FIELD LENGTH USING VARIABLE NOZZLE  
A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan...
US20090148272 TIP TURBINE ENGINE AND OPERATING METHOD WITH REVERSE CORE AIRFLOW  
A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow...
US20150104341 BYPASS VALVE, IN PARTICULAR COMPRESSOR BYPASS VALVE  
A bypass valve (1), in particular a compressor bypass valve, having a valve housing (2); a valve guide body (3), which is fixed in the valve housing (2); and a valve disk (4), which is guided...
US20140023487 GAS TURBINE ENGINE OUTER CASE WITH CONTOURED BLEED BOSS  
An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The...
US20090004032 Deswirl mechanisms and roller bearings in an axial thrust equalization mechanism for liquid cryogenic turbomachinery  
Vane, fin, and hole arrangements establish a predetermined reduced swirl at the inlet of mechanical seals and the inlet of a variable axial orifice gap which act in harmony as an axial thrust...
US20140003906 NON-INTERRUPTED TURBOMACHINE FLUID SUPPLY  
An exemplary fluid supply system for use on a turbomachine includes a turbomachine fluid container having a moveable barrier. A pressurized fluid is delivered to one side of the moveable barrier,...
US20090116955 TURBINE ENGINE COMPRISING MEANS FOR HEATING THE AIR ENTERING THE FREE TURBINE  
The invention relates to a turbine engine (10), particularly for a helicopter, comprising a gas generator (12) and a free turbine (14) rotated by a gas flow (F) generated by the gas generator. The...
US20090000306 Stator assembly including bleed ports for turbine engine compressor  
A stator assembly for a turbine engine is disclosed. The stator assembly has a stator support ring, a plurality of stator vanes protruding radially inwardly from the stator support ring, and at...
US20080101922 Asymmetric compressor air extraction method  
A method to mistune rotating stall aerodynamics by preventing the formation of coherent unsteady loads. Compressor air is extracted in an asymmetric circumferential pattern. The asymmetric bleed...
US20100126183 CMC MIXER WITH STRUCTURAL OUTER COWLING  
The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer...
US20090022579 BURN RESISTANT ORGANIC MATRIX COMPOSITE MATERIAL  
A burn resistant composite article includes at least one composite layer having first fibers within a first organic resin matrix. At least one burn resistance layer is disposed adjacent the at...
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