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| Number | Title | Issue Date |
| 4714407 | Aerofoil section members for turbine engines To minimize secondary losses and flow maldistribution, an aerofoil such as a gas turbine nozzle guide vane, is designed so that in the throat defined by the trailing edge of one aerofoil and the flank of the adjacent aerofoil, the local gas flow streamlin... | 12/22/1987 |
| 4713938 | Gas turbine engine gaseous fuel injector A gaseous fuel injector for an industrial gas turbine plant is arranged to operate on fuel produced from a coal gasifier for normal running or natural gas for starting purposes. The injector is self purging to prevent the ingestion of natural gas or combu... | 12/22/1987 |
| 4713934 | Gas turbine engine air intake An air intake for a gas turbine engine compressor comprises an arcuate primary duct which is in communication with the compressor of the gas turbine engine and which is provided with frangible wall portion. The frangible wall portion provides a barrier be... | 12/22/1987 |
| 4711085 | Gas turbine engine fuel systems A fuel system for a gas turbine engine is arranged to schedule fuel flow between primary and secondary fuel injectors in order to obtain good ignition and light round when the engine is operating on diesel fuel. The system includes either two solenoid val... | 12/08/1987 |
| 4702070 | Gas turbine engine valve control system A control apparatus for the bleed valve of a gas turbine engine compressor enables the engine to be operated with a low risk of compressor surge or stall, particularly on emergency shut down. The control apparatus includes a control valve and a diverter valve.... | 10/27/1987 |
| 4702071 | Inlet particle separator To prevent dust and other debris from entering the compressor (12) of a gas turbine engine (10) an inlet particle separator (30) is provided. Air contaminated with dust and debris is induced into a scavenge chamber (32). An exhaust vent (35) is provided f... | 10/27/1987 |
| 4699567 | Fan duct casing A containment ring for a gas turbine engine fan duct comprises a rigid cylinder the periphery of which is covered with layers of fibrous material consisting of a plurality of pieces of woven material, around which is wound a further plurality of continuou... | 10/13/1987 |
| 4698237 | Metal surface hardening by carbide formation A method of surface hardening a metal surface in which the surface is firstly coated with a colloidal dispersion of graphite and then locally melted, in an inert atmosphere or vacuum, so that the molten metal reacts with the graphite to form a metal carbi... | 10/06/1987 |
| 4697079 | Analyzing fluid flows within hollow bodies Carrier particles, e.g., of metal or metal oxide, are doped with a positron-emitting isotope and injected into fluid flowing in a body, such as a gas turbine engine. The positrons decay on coming to rest, giving two gamma rays which are detected, and a 3D... | 09/29/1987 |
| 4693074 | Combustion apparatus for a gas turbine engine The present invention relates to combustion apparatus for gas turbine engines. An annular combustion chamber of a gas turbine engine comprises an upstream wall formed from a single metal skin. The upstream wall has a plurality of equi-spaced apertures, an... | 09/15/1987 |
| 4693201 | Low drag surface construction A low drag surface construction utilizes a plurality of longitudinally extending, parallel, spaced apart linear vortices extending transversely of the free stream to reduce drag between the free stream and the surface. The surface is provided with stabili... | 09/15/1987 |
| 4691877 | Compound helicopter and powerplant therefor A compound helicopter shown in FIG. 1 of the drawings has wings 12 in addition to a helicopter rotor 14 and has twin powerplants 16 each including a low pressure compressor 18, a core engine 20, a power turbine 22 driven by the core engine and connected t... | 09/08/1987 |
| 4688995 | Propeller module for an aero gas turbine engine A propeller module for an aero gas turbine engine comprises two contra-rotating propellers driven by a reduction gearbox positioned axially between the propellers. Pitch change mechanisms operated by a pitch change power unit are provided to change the pi... | 08/25/1987 |
| 4688429 | Determination of the spectral content of transient stress wave events The spectral content of a transient stress wave event occuring on a plate-like structure is determined by locating a transducer on the surface of the structure at a position remote from the location of the transient stress wave event. Lamb waves resulting... | 08/25/1987 |
| 4685864 | Hollow aerofoil blade A hollow aerofoil cross-section aircraft propeller blade is provided with a tow of KEVLAR fibres internally thereof. The fibres which are anchored to the blade root and tip portions are arranged to be passive under all normal operating conditions of the b... | 08/11/1987 |
| 4683716 | Blade tip clearance control The invention is particularly concerned with the control of blade tip clearance in high pressure compressors of gas turbine engines. The compressor comprises a rotor assembly having radially extending rotor blades and a stator assembly. The stator assembl... | 08/04/1987 |
| 4684325 | Turbomachine rotor blade fixings and method for assembly A bladed rotor assembly for a turbomachine includes a hub having a circumferential blade retaining groove and a plurality of blades which have rhombic shaped platforms. The blade retaining groove is continuous and the blades are loaded into the groove by ... | 08/04/1987 |
| 4683018 | Composite material manufacture by shaping individual sheets followed by consolidating the sheets A composite material comprising reinforcing carbon fibres in an epoxy resin matrix is manufactured by stacking alternate layers of resin impregnated fibre and polyester release film, and compressing the stack between shaped formers at a temperature below ... | 07/28/1987 |
| 4682733 | Thrust reverser A thrust reverser for a gas turbine engine of the type to power an aircraft, the thrust reverser comprising a first pair of half round doors nesting in a second pair of half round doors and both being pivoted on an axis extending diametrically of a jet pi... | 07/28/1987 |
| 4683099 | Moulding of composite materials A method of moulding composite materials in which prepregs of resin impregnated filaments are interposed between a shaped partially contained polytetrafluoroethylene body and a die. The assembly is heated to cause the polytetrafluoroethylene body to therm... | 07/28/1987 |
| 4679394 | Gas turbine engine power plant A nozzle structure for a gas turbine power plant for a V.T.O.L. or S.T.O.L. type aircraft includes a main engine and at least one auxiliary engine; the efflux from the at least one auxiliary engine may be directed downwardly or alternatively horizontally ... | 07/14/1987 |
| 4679732 | Vectorable exhaust nozzle for a gas turbine engine A vectorable nozzle (17) comprises a fixed first duct (21), a rotatable second duct (22) scarfed at its downstream end, and a rotatable third duct (23) scarfed at its upstream end. The second and third ducts (22, 23) are mounted in bearings (24,26), respe... | 07/14/1987 |
| 4678113 | Brush seals A method of manufacturing a brush seal is disclosed which comprises producing a plurality of tufts of brush material and securing the tufts between two side plates to form a seal. Each tuft is produced by forming a tape which comprises one or more layers ... | 07/07/1987 |
| 4673124 | Method for eliminating, or minimizing the effects of, defects in materials A method is described for the manufacture of articles in defect-immunized materials in which the defects are eliminated, or broken up and oriented in such manner as to minimize their harmful effects on the article. Referring to FIG. 1e, a rotor disc for a gas ... | 06/16/1987 |
| 4671738 | Rotor or stator blades for an axial flow compressor A rotor or stator blade for an axial flow compressor has one or both of its end portions designed to minimize the interference between the annulus boundary layer and the blade. The basis of the invention is that the aerofoil is designed so that each secti... | 06/09/1987 |
| 4669955 | Axial flow turbines An axial flow turbine comprises an annular array of rotatable turbine blades which are surrounded by a shroud ring. An open honeycomb structure is attached to the shroud ring, the open cells of which honeycomb structure contain an abradable material. The ... | 06/02/1987 |
| 4666371 | Gas turbine engine having improved resistance to foreign object ingestion damage A gas turbine engine has an axial flow compressor, the inner wall of which is provided with a lining adapted to capture and retain any small hard foreign objects impinging upon it. The lining consists of an aluminum alloy sheet having a silicone rubber co... | 05/19/1987 |
| 4664600 | Rotor aerofoil blade containment A hollow prop-fan aerofoil blade is covered by a woven containment sheath which is bonded to the aerofoil surface of the blade and operationally anchored to the blade root. The sheath is arranged to be of sufficient strength to contain any of the aerofoil... | 05/12/1987 |
| 4657482 | Air cooling systems for gas turbine engines A gas turbine engine in which a rotating component (such as a turbine shaft or disc) is cooled by directing preswirled air at it by flowing the air along a passageway defined by the rotating component and a static wall. To reduce the viscous drag on the s... | 04/14/1987 |
| 4657479 | Rotor tip clearance control devices A shroud for a gas turbine engine rotor stage is divided into a number of arcuate segments each of which is a trapezium. The segments are urged together by compression springs which attempts to make the assembly lengthen peripherally, by virtue of the cha... | 04/14/1987 |
| 4651523 | Integral rocket and ramjet engine An integral rocket and ramjet engine (16) comprises, in flow series, an intake duct (18) for aerodynamically compressing air, a port cover (30), a combustion chamber (20) and a propelling nozzle (22). The port cover (30) in a first position prevents air f... | 03/24/1987 |
| 4643647 | Rotor aerofoil blade containment A hollow propfan aerofoil blade is provided with grooves which extend between its root and tip portions. The grooves contain filaments which are enclosed within a resin matrix material and are anchored to the root and tip portions. The filaments are arran... | 02/17/1987 |
| 4641782 | Jet propulsion nozzle Jet propulsion nozzle comprises a pair of mutually confronting side walls 11, a pair of mutually confronting first panels 14 extending transversely between the walls and being supported thereon for pivotal movement about a first axis 18. A pair of mutuall... | 02/10/1987 |
| 4626297 | Single-crystal alloy The invention relates to an alloy suitable for making single-crystal castings and to a casting made thereof. The alloy comprises, by weight percent, Chromium 10-16%, Cobalt 4-16%, Molybdenum 2-4%, Tungsten 0-2%, Tantalum 2-8%, the sum of ##EQU1## ... | 12/02/1986 |
| 4624820 | Molding of composite materials A method of molding a composite material comprising reinforcing fibres enclosed in a resin matrix. Layers of the resin impregnated fibres are laid-up in a suitably shaped die whereupon the laid-up layers are overlaid by a silicone rubber member which gene... | 11/25/1986 |
| 4618094 | Thrust deflection A gas turbine engine which is used for aircraft propulsion, is provided with a pair of thrust deflecting doors which, when deployed, deflect the exhaust gases onto some path other than axially of the engine, so as to spoil the thrust. The doors are waiste... | 10/21/1986 |
| 4616976 | Cooled vane or blade for a gas turbine engine A cooled vane or blade for a gas turbine engine has a cooling arrangement for its trailing region which can be accommodated in the relatively thin section available. In this arrangement the trailing region of the hollow interior of the blade is divided of... | 10/14/1986 |
| 4616932 | Method of observing change in a shape Gas turbine engine compressor blades tend to untwist and decamber when subjected to working loads. Previous methods of observing the phenomenum and recording the magnitude of distortion have been restricted to the blade outer extremity, and to delayed dis... | 10/14/1986 |
| 4610135 | Combustion equipment for a gas turbine engine Combustion equipment for a gas turbine engine operating on the pre-mix lean combustion bases comprises a flame tube having a plurality of alternately arranged main and pilot air ducts each having a respective fuel injector and receiving axially directed a... | 09/09/1986 |
