Motoren- Und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Mtu Aero Engines Gmbh

Mtu Motoren-und Turbinen-union

Mtu Munchen Gmbh

Wolfgang Weiler

Klaus Trappmann

Herbert Merz

A jet engine includes a fan arranged upstream of a core engine having a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure turbine. The high pressure turbine is drive-connected to the high pressure compressor. The low pressure turbine is drive-connected through a transmission to the low pressure compressor and to the fan, which are respectively driven in opposite rotation directions. A compressor disk of the low pressure compressor is positioned downstream directly after the fan so that a hub end section of the fan and the compressor disk together form a counter-rotating compressor stage.

Jet engine with compact arrangement of fan

A sealing arrangement for turbomachines with a shaft bearing, a throw-off ring and a shaft seal which is assigned to a sealing gap and has a seal housing wherein opposing faces of the throw-off ring and the seal housing form an annular gap for centrifuging out dirt and oil particles.

Arrangement comprising a slinger associated with a shaft bearing and a gasket associated with a sealing gap

Abradable layer for a turbo-engine and a manufacturing process

An arrangement is disclosed for the sealing-off of spaces acted upon by media of a different pressure, for turbomachines, in which a sealing ring is arranged in a cylindrical housing while forming a radial sealing gap as a primary seal, and having a secondary leakage flow passage between a wall section of the housing and the sealing ring which communicates with the space having a lower pressure, the sealing ring being centered by means of spring elements which are anchored at the housing on one side and are arranged essentially in parallel with respect to the machine axis.

Arrangement for the sealing-off of spaces acted upon by media of

A gas turbine power plant, especially for helicopters, includes a main engine and a reduction gear transmission forming a self-sufficient auxiliary modular unit. A compensating arrangement includes an articulated outer cover and a shaft section inside said outer cover connected for transmitting power and for compensating any position disalignment between the main engine and the helicopter main gear drive. The reduction gear transmission is directly, rigidly force-coupled to the helicopter main gear drive, and the compensating arrangement including the articulated outer cover and shaft section is located between the main engine and the reduction gear transmission, whereby the axial length spacing between the main engine and the helicopter main gear drive is substantially reduced.

Gas turbine power plant arrangement

A cooled gas turbine power plant has a compressor and a high pressure turbine connected to the compressor. The cooling air quantity for the turbine is controlled in response to instantaneous load conditions and in direct response to the cooling air quantity control of the compressor. This control of the cooling air quantity for the turbine is achieved by a direct mechanical coupling of a slide valve for the turbine cooling air control with the control of the compressor, whereby good power output values and low fuel consumption values are achieved for the high pressure turbine, especially under partial load operating conditions. The compressor may be controlled by an adjustment of the angular position of its guide vanes or blades or by an adjustment of the quantity of its discharge air.

Cooled gas turbine operable with a controlled cooling air quantity

A gas turbine engine is so constructed that the clearance or gap between the rotor and stator, especially at the outer diameter range of a radial flow end stage, is optimally maintained under all operating conditions. For this purpose the housing in the axial-flow/radial-flow compressor is constructed as a two shell housing. The outer housing shell is mounted as part of the engine structure, whereby the inner housing shell is exposed substantially only to forces or loads caused by compressor fluid flow. The material of the outer housing shell has a heat expansion coefficient in the axial direction of the rotational engine axis, which is distinctly lower than the heat expansion coefficient of the material of the compressor rotor. The heat expansion coefficient of the material of the inner housing shell is lower in the circumferential direction and approximately equal in the axial direction relative to the heat expansion coefficient of the rotor. The fixed bearing of the compressor rotor is arranged in the zone of the compressor inlet.

Gas turbine engine having a minimal blade tip clearance

An annular sleeve surrounds a turbine rotor and is fixed with respect to the turbine casing, the sleeve being elastically deformable in a radial direction. A wear ring is carried by the sleeve, the wear ring being composed of segments arranged end-to-end circumferentially. The adjacent ends of the segments are spaced apart when the turbine is cold or idling. The thermal expansions of the turbine rotor and of the sleeve and ring are so related that in one operating temperature range of the turbine the spaces between the adjacent ends of the ring segments close and the segment ends engage each other, and in a higher operating temperature range of the turbine the sleeve expands. Air leaving the compressor is directed against the sleeve and the stationary part carrying the sleeve. The wear ring and portion carrying the sleeve may be insulated. The sleeve may be mounted on a combustion chamber surrounding the turbine.

Arrangement for maintaining clearances between a turbine rotor and casing

An annular sleeve surrounds a turbine rotor and is fixed to a stationary part, the sleeve being elastically deformable in a radial direction. A wear ring is carried by the sleeve, the wear ring being composed of segments arranged end-to-end circumferentially. The adjacent ends of the segments are spaced apart at all operating conditions of the turbine. The thermal expansions of the turbine rotor and of the sleeve and ring are so related that under operating conditions of the turbine, when the engine of which it forms a part is running, the sleeve thermally expands radially. The rate of thermal expansion of the stationary part is directly related to the rate of thermal expansion of the turbine rotor. Air leaving the compressor is directed against the sleeve and the stationary part carrying the sleeve. The wear ring and portion carrying the sleeve may be insulated. The sleeve may be mounted on a combustion chamber surrounding the turbine.

An arrangement for operating shut-off members in gas turbine engines, particularly turbojet engines. Circumferential rotation of an actuating ring is converted into axial opening or closing movement by transmission element. These transmission elements are in the form of bellcranks which are pivotally supported in their elbow area on a fixed casing of the engine. A free arm end of each bellcrank is hinged to the actuating ring. Another free end of each bellcrank is hinged to a pull rod engaging at least one axially moveable shut-off member, or an axially adjustable shut-off element thereon. Two pull rods associated with respective shut-off members, are each pivotally connected on a side opposite the associated shut-off members at various points of an arm of the bellcrank. The arrangement is such that co-directional movement of the shut-off members produces different travels or strokes of the shut-off members.

Apparatus for operating shut-off members in gas turbine engines,

This invention relates to a variable stator cascade for axial-flow turbines of gas turbine engines, especially for high-pressure turbines, where the turbine nozzle vanes are each pivotally arranged about an axis of rotation and are cooled when in operation. The inner and outer rings of the variable stator cascade are formed of interlocking inner and outer ring segments which provide circumferential sealing action where each turbine nozzle vane is pivotally arranged and disconnectably connected by respective root and tip side pivot pins in association with each respective inner and outer ring segments. A continuous inner stator ring, is centrally located at inner ring segments of the stator cascade by means of teeth and a slot-and-key arrangement whereby each outer ring segment arranged at the turbine casing cooperates with the vane attachment assembly to radially guide the nozzle vane and associated inner ring segment. A variable stator cascade is secured in radial, axial and circumferential position by means of the respective outer ring segments. The turbine nozzle vanes have at their respective root and tip sides, vane plates arranged in the area of the inner and outer walls of a turbine duct attached to which are the pivot pins arranged outside the turbine duct and which take the shape of tubular cylindrical cooling air ducts which communicate with the interior of the vane.

Variable stator cascades for axial-flow turbines of gas turbine engines

A compressor rotor wheel construction and a method of making same is provided which includes a blade portion of heat-resistant metallic material, a rotor disk portion made of a high-strength metallic material, and a steel spacer ring arrangement connecting the blade and rotor disk portions. The steel spacer rings are connected by explosion welding to the blade portion, are then finish machined, as is the rotor portion, and then the spacer rings are connected respectively to the rotor disk portion by brazing or welding.

Compressor rotor wheel and method of making same

A gas turbine engine in which a centrifugal diffusor is located downstream of a centrifugal compressor. The compressor air flow from the centrifugal diffusor is deflected into an axial direction by a substantially 90 degree elbow. The air flow is further decelerated in an axial-flow stator cascade upstream of the combustion chamber. A main bearing of the gas generator is arranged immediately downstream of the centrifugal compressor. This bearing is supplied from the outside through vanes of the axial-flow stator cascade. The axial-flow stator cascade is divided into groups of vanes, so that each group had a number of relatively small guide vanes and one relatively large guide vane. The small guide vanes are designed from the view point of fluid mechanics consideration, while the larger guide vane of a group is hollow for supplying the bearing. The large guide vane has a substantially longer and a substantially thicker vane profile than the small vanes. Slow ducts are provided between the small vanes on the one hand, and between each small guide vane and a large guide vane on the other hand. The flow ducts are substantially of identical geometric dimensions. The large vane and small guide vanes within the cascade assembly may be arranged so that half the relative length of profile of all vanes extend in substantially one plane.

Gas turbine engine

Disclosed is a variable flow divider for a turbomachine having a gas flow channel, comprising a stationary annular casing member located within the exhaust gas flow channel of the turbomachine, thereby defining an inner flow duct and an outer, annular flow duct; a plurality of flaps pivotally mounted in the flow channel on a stationary portion of the turbomachine, including a plurality of primary flaps and a plurality of secondary flaps adapted for rotation with the primary flaps, each of these flaps rotating about an axis which is arranged at a right angle to the central axis of the turbomachine; and means, located substantially entirely within the annular casing, for rotating said flaps to vary the respective sizes of said inner and outer flow ducts in relation to one another.

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Dachau, Germany

Wolfgang Weiler