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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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.... |
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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. |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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... |
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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... |
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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... |