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WO/2008/003571A2 |
The invention relates to a method for operating a gas turbine (1) which especially feeds power to a locally isolated power supply network. Said gas turbine comprises a compressor (11) for compressing combustion air taken in from the surr...
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WO/2007/147229A1 |
An apparatus and method are provided for controlling the ground windmilling of at least one of the spools (20, 24) in a gas turbine engine (10). Electrical power is supplied to a braking apparatus (30, 32) in one aspect. In another aspec...
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WO/2007/140730A1 |
The invention relates to a gas turbine, in particular to an aircraft engine, having at least one compressor, a combustion chamber and at least one turbine, wherein at least one generator for generating electrical energy is assigned to at...
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WO/2007/124559A1 |
A containment system (22) for containing fragments of a burst rotor (20) including first and second means (52, 54) for frangibly connecting a containment element (36) to first and second walls (46, 48), the first and second means (52, 54...
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WO/2007/118452A1 |
Presentation of a device for detecting a shaft fracture in the rotor of a turbine (10), wherein at least one stator-sided sensor element (16) is positioned downstream of the turbine, particularly in the area of a stator-sided guide vane ...
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WO/2007/048996A1 |
Reduction in weight is an important factor with respect to turbine engines used in aircraft. Blades (20) used in such turbine engines may fragment such that it is necessary that the containment casing (42) can resist such fragmentation. ...
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WO/2007/044342A1 |
A turbocharger monitor including a sensor adapted and positioned with respect to a turbocharger housing to sense passing compressor blades, generating both rotor rotation information and rotor displacement information. A controller is co...
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WO/2007/036014A1 |
The emergency fuel shutoff system (20) for a gas turbine engine (10) comprises a pyrotechnic device (36) which allows the fuel circuit (22) to be closed upon triggering of the pyrotechnic device (36).
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WO/2007/033914A1 |
The invention relates to a method for monitoring the speed of rotation of a turboshaft which rotatably mounted in a turbocharger, wherein a magnetic field-modifying element is arranged on the turboshaft and generates the variation of the...
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WO/2007/035184A2 |
Described is reinforcement of a fan case (302) in a gas turbine jet engine. In one embodiment, a containment ring (702) and a hear resistance ring (1112) are shrink interference fit on the inside diameter of the fan case, the containment...
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WO/2007/028354A1 |
The invention relates to a gas turbine comprising a unit for detecting a shaft rupture in a rotor of a turbine (10), at least one sensor element (18) being positioned on the stator side downstream of the turbine (10). If a shaft ruptures...
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WO/2007/024329A1 |
Control logic (160), and a method implemented by the control logic (160), compensates for mismatched inter turbine temperatures (154, 156) between two gas turbine engines and displays a biased inter turbine temperature (ITT) reading (152...
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WO/2007/020170A1 |
The invention relates to a method for determining the layer thickness of a TBC coating of at least one blade (4, 11) of a non-positive-displacement machine (1). To this end, at least one electromagnetic wave is emitted to the surface of ...
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WO/2006/138546A1 |
A method and system for orienting and calibrating a magnet for use with a speed sensor. A magnet can be mapped two or more planes thereof in order to locate the magnet accurately relative to one or more magnetoresistive elements maintain...
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WO/2006/127159A1 |
A system and method for early detection of a failure of a gas turbine engine airfoil (10), such as but not restricted to a burn through of the airfoil outer skin (12). A sensor (52) provides a signal (54) responsive to a condition of flu...
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WO/2006/125939A1 |
An instrumentation arrangement for a component comprises a plurality of measurement devices mounted on a baseplate. The baseplate is shaped to correspond to the surface of the component in use, and has attachment features engageable with...
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WO/2006/121570A2 |
A method of instrumenting a first component (210) for use in a combustion turbine engine (10) wherein the first component (210) has a surface contacted by a second component during operation of the combustion turbine engine (10). The met...
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WO/2006/117519A1 |
A tool (12) has a flange (28) attached to an engine housing. A primary cam (20) is rotated to advance segments into the housing and a second rotational cam (22) causes the segments (16) to turn relative to each other as they are being in...
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WO/2006/061348A1 |
The invention relates to a method for monitoring the condition of turbines using their coasting time. The aim of the invention is to ensure that the monitoring process is as sensitive as possible with low resource requirements. To achiev...
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WO/2006/059971A2 |
A tip turbine engine assembly includes an integral engine outer case (8) located radially outward from a fan assembly (30). The integral outer case (8) includes a rear portion (124) and a forward portion (128) with an arcuate portion (13...
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WO/2006/057602A1 |
An axial flow turbine motor including a rotor (12) with a peripheral row of drive blades (13) and a peripheral band-shaped wall element (16) radially clamped against the tops of the drive blades (13), and a housing (10) with at least one...
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WO/2006/045680A1 |
An exhaust fume turbocharger for an internal combustion engine comprises a compressor and a turbine. A compressor wheel (9) is rotatably mounted in the compressor and a turbine wheel is rotatably mounted in the turbine. The compressor wh...
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WO/2006/045811A1 |
A method for determining an approximate value for a parameter characteristic of the fatigue state of a part as a result of a time-varying stress to which it is subjected by means of a number of load cycles should, itself, during comparat...
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WO/2006/043987A2 |
A low or high pressure turbine case is machined on its outside surface to form circumferential notches. The notches coincide with the internal locations of labyrinth seals for the blades, or with 'hot spots' that have been identified. A ...
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WO/2006/042398A1 |
A device (20) and method for measuring an area such as a throat area (10) in a vane ring (8) for gas turbine engines. Measurement inaccuracy introduced by image size changes as a result of the position deviation of the selected throat (1...
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WO/2006/037286A1 |
Disclosed is a gas turbine comprising at least one compressor, at least one turbine, and a combustion chamber to which fuel can be supplied via a fuel pump. Said gas turbine can be shut off when breakage of a shaft which couples a compre...
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WO/2006/034132A2 |
An impeller for moving liquid through a pump system having a body, at least one vane extending from the body and capable of moving liquid through the system during rotation thereof, and a tapered, abradable tip extending from the vane wh...
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WO/2006/029965A1 |
The invention relates to an exhaust gas turbo charger for an internal combustion engine, comprising a compressor and a turbine. A compressor wheel is rotationally mounted in the compressor and a turbine wheel is rotationally mounted in t...
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WO/2006/021078A1 |
A braking apparatus (34) for an aircraft gas turbine engine (10), the engine having concentric first and second shafts (22, 26) with first and second turbine stages and first and second compressor stages respectively mounted thereto, the...
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WO/2006/023689A1 |
A diagnostic system (10) and method for testing the operation of a rotary flow device (70), such as a turbine (80) or compressor (90) of a turbocharger with a variable geometry mechanism, such as adjustable vanes (88, 98), is provided. T...
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WO/2006/005662A1 |
The invention relates to an exhaust-gas turbocharger (1) for an internal combustion engine, said turbocharger comprising a device (26) for detecting the speed of the turbocharger shaft (5). The device (26) for detecting the speed compris...
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WO/2006/005712A1 |
Disclosed are a method and a device (1) for monitoring the cooling air system (3) of a turbine (5), cooling air (9) being fed to at least one series of blades (7) of the turbine (5). According to the inventive method and the inventive de...
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WO/2005/119030A1 |
The inventive turbine comprises a cooled turbine wheel. The hub (11) of the turbine wheel is cooled by means of a cooling channel (50) that is configured in the neighbouring turbine housing (22). The lower material temperatures thus achi...
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WO/2005/119012A1 |
The subject invention is directed to a control system for a turboshaft engine utilized in a helicopter which includes means for providing minimum fuel flow to the engine when an overspeed condition is detected at a relatively low altitud...
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WO/2005/119294A1 |
The invention provides a sensing system and a method for monitoring the damage to turbine components in a turbine generator. The sensing system comprises an electromagnetic wave generator that generates an electromagnetic wave; a transmi...
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WO/2005/116406A1 |
The invention relates to a device for detecting a fracture in the shaft of a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine, especially an aircraft engine, a second turbine (11), especially a low-pressur...
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WO/2005/113962A1 |
An engine shutdown device for controlling a fuel shut-off valve to thereby selectively interrupt fuel flow to an engine. The device comprises a normal switch connected to the fuel shut-off valve and configured to respond to at least one ...
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WO/2005/111412A2 |
A self-calibrating, continuous variable speed fan for use in cooling electronic circuitry is disclosed. Upon initial power-up, in an environment of known temperature, the self-calibrating fan accommodates for the tolerances on its electr...
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WO/2005/105370A1 |
An over- speed safety device for a pneumatic rotation motor having a cylinder (10), a forward end wall (11), a rear end wall (12) with a pressure air inlet opening (21), a rotor (13), and an actuator (15) co-rotative with the rotor (13) ...
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WO/2005/093221A1 |
The array and method are used to detect damages of a component (4) of a jet engine (1). A measuring line (9) for detecting a measurable variable extends partly through the interior of the component (4) so the damage of the component (4) ...
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WO/2005/093220A1 |
The invention relates to a rotor (3) of a non-positive-displacement machine which, when exposed, has an inspection area (29) which is visible from the outside and inside of which a comparatively uncritical load occurs during the operatio...
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WO/2005/086864A2 |
An enclosure comprising elements for air management, sound attenuation and fire suppression in a trailer-mounted mobile electrical power generation system. Air management is provided by ducts, fans, seals and a barrier wall. In addition,...
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WO/2005/083237A1 |
The invention relates to a method for identifying a shaft fracture and/or an excessive rotational speed in a gas turbine, especially in rotating parts of an aircraft engine. According to the invention, the integrity of at least one devic...
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WO/2005/080937A1 |
The microstructure of components (4), particularly layer systems, deteriorates under excessive thermal and/or mechanical stress. Previous test methods are destructive, parts being cut out of the layer system and being microstructurally a...
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WO/2005/073667A1 |
An apparatus and a method for measuring the clearance between the blade tips of the compressor blades of a rotatable compressor assembly and the housing in which the compressor assembly is mounted in a gas turbine engine are disclosed. T...
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WO/2005/054873A1 |
A method and apparatus is disclosed for sensing rotation of a rotating body involving a generating signal in response to a intermittent modification of a magnetic field caused, for example, by a moving of a finite body through the field.
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WO/2005/054646A1 |
There is provided a gas turbine protection device capable of outputting a gas turbine protection signal only when a burner is in an abnormal state without increasing the number of temperature sensors such as thermocouples. For this, a BP...
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WO/2005/052341A1 |
Procedure for controlling the useful life of the gas turbines of a plant by means of a production plant (10) equipped with a series of production trains (15) and an auxiliary gas generator group (40). Each production train (15) is in tur...
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WO/2005/019603A1 |
The invention relates to a method for braking a rotor (3, 30) of a turbine engine (31), comprising a turning gear (22), with a drive supplied from an energy source, having an input shaft (28) to which the rotor (3, 30) may be coupled, wh...
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WO/2005/012919A1 |
A turbocharger includes a cylindrical wall and a non-ferromagnetic compressor wheel within the cylindrical wall. The non-ferromagnetic compressor wheel has fins. A magnetoresistive sensor housing is threaded through the cylindrical wall ...
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