Abstract: A gas turbine electric powerplant, preferably driven by an aeroderivative turbine engine of split shaft design. The gas turbine engine is coupled to a speed reducer, which is in turn coupled to an electric generator. An engine mount is provided that ensures that the gas turbine engine will remain in proper alignment with the speed reducer and generator, even during the thermal expansion or contraction thereof. Preferably, the components comprising the powerplant are mounted to a common, transportable base, so that the powerplant can be delivered to various locations. An overspeed control system is provided for ensuring that a runaway condition of the gas turbine engine does not occur should the gas turbine engine become disconnected from the speed reducer or generator. Sensors are used to monitor multiple operating conditions of the powerplant.

Abstract: This invention relates to a mounting structure (1) for mounting an engine (2) under an aircraft wing (4), the structure comprising a rigid structure (8) and means (10) of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (14), an intermediate fastener (15) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine (2), placed in a vertical plane oriented along a longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: An integrated mount duct includes a load ring for mounting a turbomachine to a flight vehicle, wherein the load ring has a cylindrical shape with a flange edge and a stepped edge, and comprises one or more mechanical attachment members disposed on an outside surface of the load ring, the mechanical attachment members configured to mate with a strut.

Abstract: A gas turbine power generator plant, intended to reduce its noise by making small the intake and exhaust outlets of the cooing air channel of a case, comprises an engine core in which a turbine, a compressor and a generator are installed on the same axis, a combustor for burning air for combustion compressed by the compressor and supplying the air to the turbine, a radiator for cooling a coolant or a lubricant, a cooling fan for ventilating the radiator with cooling air, an electric power converter for converting electric power generated by the generator, and the case for housing these constituent elements. And, a combustion air channel passing the compressor, the combustor and the turbine and a cooling air channel passing the radiator, the cooling fan and the electric power converter are formed as mutually independent channels from intake to exhaust.

Abstract: An aircraft engine attachment configured to be inserted between an engine and an EMS, the attachment including a clevis connected to a first fixing device including an end fitting with two arms and a pin passing through the clevis and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin. The first ring includes a bottom acting as a stop for a first end of the pin, and the first attachment device includes a mechanism to stop the pin in translation cooperating with a second end of the pin.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.

Abstract: A method for assembling a gas turbine engine assembly that includes mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module, coupling a first deflector within the module engine area such that when cooling air is channeled past the deflector, the deflector induces a substantially helically-shaped cooling air flowpath around a periphery of the gas turbine engine, and coupling an exhaust duct to an outlet of the module exhaust area.

Abstract: A casing for a gas turbine includes a fan case, an intermediate case and a gas generator case integrated with one another.

Abstract: A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support plane (P), which is perpendicular to an engine centerline (A). The shaft (60) is rotationally fixed, coaxial with the engine centerline (A), and structurally supported by the engine support structure (12) such that a load borne by the shaft (60) is transferred along the engine support plane.

Abstract: An aircraft engine mounting assembly comprising a bracket arrangement with two plates located either side of an opening in the structural bypass duct. The bracket arrangement mounts two inclined links which connect to the engine. In normal usage, tension/compression from the links will be passed by the bracket arrangement into the airframe. Upon failure of one of the links the bracket arrangement will engage with the structural bypass duct to transmit engine loads into the airframe via the duct.

Abstract: A mounting assembly (10) for mounting a gas turbine engine on an aircraft. The assembly (10) comprising four equispaced hydraulic piston and cylinder thrust links (16) connecting between the engine fan case (12) and the air intake (14), which intake (14) is mounted to the airframe.

Abstract: A structure for mounting a turboprop under an aircraft wing includes a rigid structure and a device for fastening the turboprop on the rigid structure. The rigid structure is composed of a box, and the device for fastening includes at least two lateral connecting rods resisting the engine torque generated by the turboprop, the connecting rods being arranged on each side of the box and each having a forward end connected to a gear box of the turboprop, and an aft end connected to the box.

Abstract: A combustor assembly for a gas turbine engine comprises a casing arrangement defining an aperture and a seal element mounted on the casing arrangement through which a component of the combustor can extend. The seal element comprises a relatively flexible force absorbing portion and a relatively rigid sealing portion. The force absorbing portion is provided between the sealing portion and the casing arrangement. The force absorbing portion is resiliently deformable to absorb force during movement of the casing arrangement. Such resilient deformation restricts transmission of the forces to the sealing portion. The seal element may be configured to carry a seal member.

Abstract: A front attachment device for attaching an aircraft engine to an aircraft pylon includes an upper brace fitted with elements rigidly fastened to the pylon and first and a second connecting rods, each connected to the engine, via a first ball joint connection at one end portion and to the upper brace via a second ball joint connection on the other end portion. The device further includes in each connecting rod a third stand-by link. The first and second connecting rods are interchangeable with each other.

Abstract: A turbine power plant includes power generation apparatuses divided into a plurality of modules, a common base mounting thereon the power generation apparatuses and a supporting apparatus for supporting the common base. The common base is constructed so as to be commonly used as a part of a transportation vehicle and as a frame of the power plant.

Abstract: A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.

Abstract: A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.

Abstract: An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced from the body or airframe of the aircraft.

Abstract: This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of an attachment strut, the system particularly comprising a thrust resistance device (20). The thrust resistance device (20) comprises two lateral actuators (30) each provided with a rod (34) in which a forward end (34b) is a piston located inside a chamber (38) of a central casing (22) of the engine, the chamber (38) comprising a forward compartment (40) and an aft compartment (42). Moreover, the thrust resistance device (20) comprises a device (32) including a piston (48) fixed to the forward mount (16) and located inside a chamber (50) fixed to the central casing, the chamber (50) comprising a forward compartment (52) and an aft compartment (54), the forward compartment (52) of the chamber (50) being hydraulically connected to the aft compartments (42) of the actuators (30).

Abstract: A turbine engine mount to a pylon of an aircraft includes a bracket arranged to be attached to the pylon, and a lever attached in its central part to the bracket via a first connection and two thrust links each joined aft to the lever by a second connection. The lever includes a central part with two arms, and the bracket includes an integral attachment lug placed between the two arms and connected to the arms via a pivot pin to form the first connection. The lever is laterally connected to the bracket via pivot pins passing through the lever and mounted with a clearance to form connections on standby.

Abstract: A suspension part for mounting a turbojet engine includes two ends equipped with two elements, juxtaposed in a widthwise direction of the suspension part, for fixing the suspension part to the fixed structure. The ends are shaped into pairs of yokes respectively flanking connecting rods and each including fixing elements and a bearing of a journal of a connecting rod which bearing is situated underneath a fixing element. The suspension part also includes slots passing through the two ends of the suspension part and running between the yokes without running over a central portion of the suspension part. Each of the yokes has an upper portion with an additional thickness located on an inside of each of the yokes.

Abstract: A method to ventilate a rotary machine housed in a compartment having a ventilation air inlet and air exhaust, a variable speed ventilation fan and a temperature sensor, wherein the method includes: sensing a temperature level of the rotary machine; applying the sensed machine temperature level to a controller for the fan; drawing ventilation flow through the compartment and over the machine; determining whether the sensed machine temperature level is above a desired temperature level of the rotary machine, wherein the desired temperature level is determined by the controller, and the controller setting an operational condition of the fan to increase the ventilation flow through the compartment if the sensed machine temperature level is above the desired temperature level.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, and coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine. In addition, the method also comprises coupling an infrared suppression system in flow communication with the engine exhaust nozzle for channeling exhaust gases discharged from said exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine during operation, wherein the infrared suppression system includes an access door and a flow channel that is coupled to the access door such that the flow channel is movable with the access door from a closed position to an open position.

Abstract: A connector that receives a threaded apparatus and reduces stresses induced from the treaded apparatus into the connector is described. The connector includes a top side, a bottom side, and an opening that extends therethrough. The opening is defined by an inner surface that includes a threadform including a plurality of threads. The threads extend radially outward from the inner surface into the connector opening and include a first thread portion and a cutback that extends through a portion of the threadform. The cutback facilitates less stresses being induced into the first thread portion.

Abstract: A turbine power plant comprises power generation apparatuses divided a plurality of modules, a common base mounting thereon the power generation apparatuses and a supporting apparatus for supporting the common base, and is characterized by a construction of the common base, constructed so as to be commonly used with a part of a transportation vehicle and a frame of the power plant.

Abstract: Aircraft engine comprising a pod comprising, in sequence from front to back, an air inlet structure (6), fan cowls (7), thrust inverter cowls (8), and a nozzle (9), additional stiffening means are placed either in the air inlet structure (6) or between the fan cowls (7) and the thrust inverter cowls (8). This arrangement limits the clearance between fan cowls (7) and thrust inverter cowls (8), despite the pressure differences applied in flight on the air inlet structure (6), due to the aerodynamic air flow. This avoids the formation of an excessive parasite drag that would increase engine fuel consumption.

Abstract: The present invention relates to a turbogroup (1) of a power generating plant. A turbine unit (2), has a turbine (4) and a further fluid-flow machine (6) on a common turbine shaft. A generator unit (3), has a generator (8) on a generator shaft (9). The turbine shaft (5) and the generator shaft (9) are connected to one another. A third radial bearing unit (13) supports the generator shaft (9) on a side of the generator (8) which faces the turbine unit (2). A thrust bearing unit (16) supports the turbine shaft (5) axially between the generator (8) and the additional fluid-flow machine (6). The thrust bearing unit (16) and the third radial bearing unit (13) are integrated in a common bearing block (17) which is firmly connected to a fixed foundation (18).

Abstract: A method enables a thrust link including a clevis to be coupled to a mounting lug including a spherical bearing. The method comprises positioning the spherical bearing within the thrust link clevis, and coupling the thrust link to the mounting lug by inserting a fastener through the clevis such that the fastener extends from one side of the clevis through the spherical bearing to the other side of the clevis, and such that fuse element included with at least one of the fastener and the clevis is positioned within a structural load path defined between the clevis and the thrust link, wherein the fuse element is configured to fail when subjected to a predetermined load.

Abstract: A sole plate in use for turbine capable of realizing a smooth sliding on a gland pad used in the mounting portion of power generating plant equipment, effectively suppressing a variation in the alignment of a rotating shaft by a reaction due to thermal expansion and the thrust of a gas turbine, and eliminating a regular maintenance such as filing of lubricating oil, and disposed between the gland pad installed on a base and a turbine support part, comprising a sole plate body made of a metal material disposed on the turbine support part sole and a sliding member made of a material with self-lubricity formed on the surface of the sole plate body on the gland pad side.

Abstract: A turbine power plant comprises power generation apparatuses divided a plurality of modules, a common base mounting thereon the power generation apparatuses and a supporting apparatus for supporting the common base, and is characterized by a construction of the common base, constructed so as to be commonly used with a part of a transportation vehicle and a frame of the power plant.

Abstract: The present invention relates to a turbogroup (1) of a power generating plant. A turbine unit (2), has a turbine (4) and a further fluid-flow machine (6) on a common turbine shaft. A generator unit (3), has a generator (8) on a generator shaft (9). The turbine shaft (5) and the generator shaft (9) are connected to one another. A third radial bearing unit (13) supports the generator shaft (9) on a side of the generator (8) which faces the turbine unit (2). A thrust bearing unit (16) supports the turbine shaft (5) axially between the generator (8) and the additional fluid-flow machine (6). A first radial bearing unit (11) and/or a second radial bearing unit (12) have/has pendulum supports (20) which are in each case supported on a bearing pedestal (21). At least one of the pendulum supports (20) is supported on the associated bearing pedestal (21) via a spring element.

Abstract: An aircraft engine turbine frame includes a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of the first structural ring about a centerline axis. A plurality of circumferentially spaced apart struts extend between the first and second structural rings. Forward and aft sump members having forward and aft central bores are fixedly joined to forward and aft portions of the turbine frame respectively. A frame connecting means for connecting the engine to an aircraft is disposed on the first structural ring. The frame connecting means may include a U-shaped clevis. The frame may be an inter-turbine frame axially located between first and second turbines of first and second rotors of a gas turbine engine assembly. An axial center of gravity of the second turbine passes though or very near a second turbine frame bearing supported by the aft sump member.

Abstract: A connector assembly for mounting turbomachinery including a link connector to be coupled to a clevis. The clevis includes a pair of arms and an opening that extends therethrough. The link connector includes a first end that includes an elastomer portion that defines an opening. The connector assembly further includes a support washer having an opening extending therethrough adjacent the link connector elastomer portion, and a fastener inserted through the clevis opening, the support washer opening, and the link connector elastomer opening to couple the link connector and the support washer to the clevis such that the link connector is coupled between the clevis arms by the fastener, and such that the support washer thermally insulates at least a portion of the link connector elastomer portion.

Abstract: This device is designed to transmit lateral and vertical forces generated by the engine to the nacelle stub (10), together with the engine torque, and comprises a main attachment structure and an emergency attachment structure (38). The main attachment structure includes two half-fittings (18a, 18b), connecting rods (20a, 20c) connecting the two half-fittings to the engine and attachment devices for the half-fittings on the nacelle stub. The emergency attachment structure transmits forces between one of the two half-fittings and the nacelle stub when the other half-fitting or its devices for attachment to the nacelle stub are defective. For example, it comprises a hinge pin (42) supported by the nacelle stub and passing through a hole (44) formed in the half-fittings with a clearance.

Abstract: A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

Abstract: A trailer mounted mobile power generation system provides electrical power at locations where it is needed, either separate from or as a supplement to power from an electrical power distribution grid. A jet engine, a free turbine and an electrical power generator in a single common road transportable trailer. The trailer complies with weight and height limitations imposed by transportation authorities. The jet engine drives the turbine, which in turn drives the electrical power generator. Power levels on the order of 20 megawatts are generated while maintaining noise and combustion product emission levels within presently specified regulatory limits.

Abstract: A power generating plant comprises: a boiler; a steam turbine to be driven with steam generated in the boiler; a power generator to be driven according to the rotation of the steam turbine; a strut for supporting the boiler; a base mounting the steam turbine thereon; and a frame for supporting the base. The steam turbine is disposed above the boiler, and the strut for supporting the boiler is used as the frame. Thus, it is possible to package the steam turbine equipment and the boiler, thereby reducing a construction site for the power generating plant.

Abstract: A turbine power plant comprises power generation apparatuses divided a plurality of modules, a common base mounting thereon the power generation apparatuses and a supporting apparatus for supporting the common base, and is characterized by a construction of the common base, constructed so as to be commonly used with a part of a transportation vehicle and a frame of the power plant.

Abstract: A boiler installation supporting frame structure supported by a supporting structural body and a gas turbine frame base are constituted integrally, and a gas turbine device is disposed at upper portion of the integrated type frame structure and at the lower portion thereof a boiler installation is disposed in a three dimensional structure. Thereby, through the three dimensional arrangement of the gas turbine device and the boiler installation, the power generation installation can be disposed in a limited space.

Abstract: The present invention relates to a turbogroup (1) of a power generating plant. A turbine unit (2), has a turbine (4) and a further fluid-flow machine (6) on a common turbine shaft. A generator unit (3), has a generator (8) on a generator shaft (9). The turbine shaft (5) and the generator shaft (9) are connected to one another. A third radial bearing unit (13) supports the generator shaft (9) on a side of the generator (8) which faces the turbine unit (2). A thrust bearing unit (16) supports the turbine shaft (5) axially between the generator (8) and the additional fluid-flow machine (6). A first radial bearing unit (11) and/or a second radial bearing unit (12) have/has pendulum supports (20) which are in each case supported on a bearing pedestal (21). At least one of the pendulum supports (20) is supported on the associated bearing pedestal (21) via a spring element.

Abstract: The present invention relates to a turbogroup (1) of a power generating plant. A turbine unit (2), has a turbine (4) and a further fluid-flow machine (6) on a common turbine shaft. A generator unit (3), has a generator (8) on a generator shaft (9). The turbine shaft (5) and the generator shaft (9) are connected to one another. A third radial bearing unit (13) supports the generator shaft (9) on a side of the generator (8) which faces the turbine unit (2). A thrust bearing unit (16) supports the turbine shaft (5) axially between the generator (8) and the additional fluid-flow machine (6). The thrust bearing unit (16) and the third radial bearing unit (13) are integrated in a common bearing block (17) which is firmly connected to a fixed foundation (18).

Abstract: A gas turbine engine assembly including a gas turbine engine mounted within a module and including an inlet in flow communication with a module inlet area and a module exhaust area is described. The turbine engine also includes an exhaust, and is mounted within an engine area between the module inlet and exhaust areas. More specifically, the gas turbine engine is mounted such that the engine exhaust is in flow communication with the module exhaust area. Because the module also includes a secondary supply duct, the gas turbine engine is in flow communication with the module inlet and exhaust areas.

Abstract: A boiler installation supporting frame structure supported by a supporting structural body and a gas turbine frame base are constituted integrally, and a gas turbine device is disposed at upper portion of the integrated type frame structure and at the lower portion thereof a boiler installation is disposed in a three dimensional structure. Thereby, through the three dimensional arrangement of the gas turbine device and the boiler installation, the power generation installation can be disposed in a limited space.

Abstract: A system for mounting an aircraft engine to an aircraft includes four forward mounting features, two mid mounting features, and four aft mounting features disposed on the engine. The forward, mid and the aft mounting features, respectively, are equally spaced circumferentially about the engine. The method of mounting the engine includes connecting the first and fourth forward mounting features to mounting structure, the first and fourth aft mounting features to mounting structure, and the first and second mid mounting features to mounting structure when the aircraft engine is used in a top mounted installation.

Abstract: Non-thermal plasma gas treatment is combined with selective catalytic reduction to enhance NO.sub.x reduction in oxygen-rich vehicle engine exhausts.