| Document |
Document Title |
|
WO/2004/113161A1 |
A drive apparatus (10) for propelling a vehicle across a body of water is described. The apparatus (10) comprises a prime mover, for example a gas turbine engine (12), and a propelling arrangement (26) driven by the prime mover for prope...
|
|
WO/2004/099658A1 |
The invention concerns a drive mechanism for a turbine valve, in particular a regulating valve and a control valve, and comprising a valve stem provided with a valve cone, actuated by an electric/transmission motor unit and designed to a...
|
|
WO/2004/090290A2 |
Disclosed is a thermal turbomachine comprising at least one series of impeller blades (1). At least one first impeller blade (1) has a greater radial length than the other impeller blades and is provided with a first abrasive layer (72) ...
|
|
WO/2004/070170A1 |
A template for assessing damaged areas on a blade includes a set of marks indicating the maximum areas of damage allowed on an edge, as well as the tip of a blade. A guide enables the template to be aligned in proper position against the...
|
|
WO/2004/065918A2 |
The method serves to determine the vibrational state of turbine blades (4), arranged on a rotor shaft, mounted such as to rotate in a housing and/or of guide vanes. At least one electromagnetic wave (31) is transmitted into a flow channe...
|
|
WO/2004/063534A1 |
During the operation of a turbine it is important that the gap between turbine blades and the turbine housing does not become too large. There is no conventional method for the detection of material abrasion on a turbine blade during ope...
|
|
WO/2004/055340A1 |
A corrected parameter control method for a two-shaft gas turbine, of the type in which the protection of the said turbine is provided by a first control loop which controls the opening of fuel valves to keep the gas temperature Tfire at ...
|
|
WO/2004/046522A2 |
The present invention provides a miniature gas turbine engine for power generation. The engine has a highly integrated unitary rotor shaft where turbine, compressor and shaft are made in one piece in one fabrication process. The turbine ...
|
|
WO/2004/042199A2 |
The turbo engine (1) comprises rotor blades (4) made of an electrically conductive material with an electrically insulating surface (5), said rotor blades being rotatably mounted on a rotor shaft (3) arranged in a housing (2). The electr...
|
|
WO/2004/033858A1 |
A turbomachinery apparatus. A turbine (10) is provided with a retainer (20) having a bore step element for turbine wheel retention, and with an aperture manifesting a tailored diameter (d) less than the trim diameter (DTRIM) of the turbi...
|
|
WO/2004/022927A1 |
A fan blade fragment containment assembly for a gas turbine engine having a fan case surrounding the fan and having a circumferential axially extending blade fragment impact zone. An inner relatively slack or low tension deformable layer...
|
|
WO/2004/018845A1 |
An energy absorber and deflection device for deflecting engine debris (7) fragments from their tangential trajectory from a core of a gas turbine engine. The device includes a deflection plate (8) radially spaced from a protected portion...
|
|
WO/2004/015273A1 |
A compressor impeller (16) for use with a boreless turbocharger (12) is provided in accordance with this invention. The compressor impeller comprises an integral hub (30) projecting axially therefrom that includes a partial bore (34) the...
|
|
WO/2004/012155A1 |
A method and device for determining the condition of a turbine blade (2, 4) in a compressor and utilizing the collected information in an estimation of the lifetime of the turbine blade (2, 4), wherein a measured value reflecting the con...
|
|
WO/2004/007915A1 |
The invention relates to a device for recentring a rotor shaft (1) in relation to the X axis of a stator structure (3) in the event of decoupling caused by excessive unbalance. Under normal operating conditions, the aforementioned shaft ...
|
|
WO/2004/007927A2 |
The invention relates to a method for influencing and controlling the oxide layer on metallic components of a hot CO2/H2O circulating system, in particular for CO2/H2O gas turbine units, whereby a carbonaceous fuel is burnt with oxygen a...
|
|
WO/2004/005675A2 |
According to the inventive method, excessive load changing speeds (10) are to be detected during the operation of the turbine (3). In the event of excessive load changing speeds, at least one turbine valve (15) of the turbine (3) is mome...
|
|
WO/2003/104630A1 |
A turbine comprising a rotor (1) driven by gas and a housing (2) enclosing the rotor. The turbine comprises a component (6) suspended from the housing (2), which component (6) is arranged inside the housing (2) and at least partially bes...
|
|
WO/2003/102494A2 |
A method and apparatus for monitoring gas turbine exhaust for unwanted flames employs a system comprising an electro-optics module (40), sensors (44), processing electronics (45), and collection and transmitting optics (20, 30). Informat...
|
|
WO/2003/095801A1 |
In a gas turbine engine, a capacitive sensor is used for measuring a tip clearance of a radial compressor section (13) thereof, and an actuator (25) is used for axially displacing a rotor shaft (12, 20) in response to an output from the ...
|
|
WO/2003/093652A2 |
The broken shaft detection system and method uses a detector assembly mounted downstream of a power turbine wheel of a gas turbine engine to detect rearward axial motion of the wheel and thereby a broken shaft event. The detector assembl...
|
|
WO/2003/087541A1 |
The invention relates to a turbo charger (1) comprising a turbine (2) and a compressor (3) which is connected to the turbine (2). The turbine (2) contains a turbine wheel (4) and the compressor (3) contains a compressor wheel (7) which a...
|
|
WO/2003/076780A1 |
A method for operating a turbine, which is arranged in a compressed air energy storage power plant, involves a controlling of an airflow using an open control loop whereby acting within a lower turbine rotational speed range, and involve...
|
|
WO/2003/074950A1 |
The invention relates to a turbo-refrigerating apparatus comprising a compressor, an air-drying block, a recuperative heat exchanger, a lubrication system, a control system and a turboexpander. The inventive apparatus is characterised in...
|
|
WO/2003/069129A1 |
The present invention relates to a steam turbine protection equipment for power plant. The equipment includes a check valve, a clutch, a valve flapper inspection device and a control system. The spindle of the valve body is joined to the...
|
|
WO/2003/048546A1 |
One or more particle arrestor rings are mounted in a curved radial flow portion of a gas turbine annular flow passage. The arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the ...
|
|
WO/2003/042504A1 |
The invention concerns an aircraft turbojet comprising a fan (9) whereof the hub (8) is driven by a shaft on at least a bearing linked to the turbojet structure through a bearing support with an interposed uncoupling device, said hub com...
|
|
WO/2003/038241A1 |
The invention relates to a system of arranging a rotating shaft which bears a piece of equipment at one end thereof and which extends backwards from said piece of equipment. The aforementioned shaft (1) is supported by a first bearing (2...
|
|
WO/2003/036050A1 |
Sectors (16) of synchronizing ring blades are maintained against tangential rotational movements by sliding into the grooves (18) of a casing (15) by pins (23) passing through perforations in the extension of said two parts, and retained...
|
|
WO/2003/023207A1 |
A method and apparatus for sealing a radial gap (27) between coaxial inner and outer rotating shafts (26, 28) of a gas turbine engine includes using a radial seal (64) as a main seal to seal the gap (27) for a normal engine operation con...
|
|
WO2002029225A9 |
Upon shutdown of a liquid fuel turbine engine, the liquide fuel supply is turned off and compressed air is passed through the fuel lines and fuel injectors to purge all remaining liquid fuel into the combustion chamber to be combusted th...
|
|
WO/2003/008766A1 |
A turbine controls testing device is disclosed that can be adapted to test the control systems of most turbine rotors without the use of steam. The turbine controls testing device comprises an operator control system, a drive motive powe...
|
|
WO/2002/090722A1 |
The invention relates to a turbocharger (12) comprising a radial compressor, in which, in the event of a compressor wheel bursting, housing parts (28, 20) or components (32) fixed to the compressor housing (24, 26, 28) are prevented from...
|
|
WO/2002/081884A1 |
The invention relates to a gas turbine (1) comprising a first compressor (2), a combustion chamber (16) and a first turbine (11), the turbine being adapted to drive the compressor via a first shaft (10a, 10b). The gas turbine also compri...
|
|
WO/2002/031332A1 |
A rotor overspeed protection system (40) for a gas turbine engine (10) controls engine fuel flow to prevent an engine rotor from over-speeding. The engine fuel metering system (42) includes a fuel metering valve (46) in flow communicatio...
|
|
WO/2002/027150A1 |
The present invention concerns an external emergency system for a gas turbine, comprising a generator (1) and a compressor (2). A fan (8) is arranged to furnish cooling air and barrier air to the generator (1). During an emergency state ...
|
|
WO/2002/025064A2 |
An inspection apparatus (40) for in-situ leak testing of the bell seal (30) of a steam turbine (10). The apparatus includes a pair of inflatable bladders (48,52) for defining a sealed volume having the bell seal (30) as its only leakage ...
|
|
WO/2001/057364A1 |
A frangible cover (22) is provided for a recess (20) in a containment case (18) for turbofan engine blade (12) removal and access. The recess (20) provided in the containment case (18) allows outward radial movement of the engine fan bla...
|
|
WO/2001/057366A1 |
According to the invention, the thermal load to which a turbine (4) is subjected is kept within an acceptable range by monitoring the change in temperature (T) of the medium that is supplied to the turbine (4), especially fresh steam, ov...
|
|
WO/2001/044625A1 |
The invention is a hardwall fan case for encasing a forward fan in a gas turbine engine. The fan case has a stiff annular shell spaced radially outward from the tips of the fan blades and a flexible ring which is an integral structural p...
|
|
WO/2001/025598A1 |
Preferably a turbofan engine includes a fan blade (22), rotatably mounted within a generally cylindrical casing (18) for rotation about a lengthwise extending central axis. An annular lining (24, 26) is mounted within the casing between ...
|
|
WO/2001/023725A1 |
A service life management system comprising one server system and a plurality of client systems hooked up together over an intranet, wherein the server system manages a remaining life evaluation and a service life of a high-temperature p...
|
|
WO/2000/073762A1 |
The invention relates to a remote-control inspection device (21) for an annular combustion chamber (5) of a gas turbine (1). Inspection is carried out by means of a video camera (33). Said inspection device (21) significantly cuts inspec...
|
|
WO/2000/050739A1 |
An apparatus is provided for use in monitoring for destructive wet compression power augmentation-related casing distortions in an industrial gas turbine equipped with and employing wet compression power augmentation, comprising: an oute...
|
|
WO/2000/046489A1 |
A hardwall fan case (1) for encasing the radial periphery of a forward fan (2) in a gas turbine engine, including a rigid annular shell (14) with a rigid hardwall fore section (15) and coated with a fore layer (16) of abradable material....
|
|
WO/2000/036280A1 |
The invention relates to a method of recognition of a shaft rupture in a turbo-engine with the purpose of initiating a suitable speed range limiting measure, especially an emergency shut-down of the fuel supply in a gas turbine system of...
|
|
WO/2000/034628A1 |
The present invention relates to an impeller containment system for containing the burst of an impeller or the burst of impeller fragments from an impeller hub. The containment system utilizes a catcher (60, 62) extending from the shroud...
|
|
WO/2000/026508A1 |
A steam turbine installation (2) provided with a steam chamber (40, 42) and a measuring sensor (52) also includes a connection between a steam chamber (40, 42) and a measuring sensor (50). Said connection should require little technical ...
|
|
WO/2000/017577A1 |
A unique and useful dynamic control system for the control of a catalytic combustion system for use on a dynamic plant, preferably, a gas turbine engine (14). The dynamic control system facilitates the replacement of conventional flame c...
|
|
WO/2000/006969A1 |
An imaging apparatus (10) for examining an object (12) having smooth surfaces is used to determine shape deformations in the surface of object (12). The imaging apparatus (10) includes an imaging device (20) for obtaining a scanned image...
|
