1872results about "Turbine/propulsion lubrication" patented technology

A gas turbine engine having a mid turbine frame comprising an annular outer case providing a portion of an engine casing; an interturbine duct (ITD) disposed within the outer case, the ITD including outer and inner rings radially spaced apart one from another and being interconnected by a plurality of radially extending and circumferentially spaced hollow strut fairings, the inner and outer rings co-operating to provide a portion of a hot gas path through the engine; a tube for delivering or discharging a lubricant fluid to or from a bearing housing, the tube extending radially through one of the hollow struts; and an insulation structure radially extending through one said hollow strut fairing, the insulation structure surrounding the tube and being spaced apart from the tube and from a hot internal surface of the one hollow strut fairing for shielding the tube from heat radiated from the hot internal surface of the one hollow strut fairing and for preventing the lubricant fluid from contacting the hot internal surface of said one hollow strut fairing when lubricant fluid leakage occurs.

Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air/fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.

The invention discloses continuous large-power turbine fracturing equipment. The large-power turbine fracturing equipment comprises a turbine engine, a reduction box, a transmission shaft and a plunger pump, wherein the turbine engine and the reduction box are arranged on the same straight line; the reduction box is connected to the plunger pump through a transmission shaft; and an angle of the transmission shaft ranges from 2 degrees to 4 degrees. The continuous large-power turbine fracturing equipment has the beneficial effects that: a chassis T1 material is selected, so that a stable working platform is provided for the equipment; the turbine engine and the reduction box are on the same straight line, the transmission shaft is arranged between the reduction box and the plunger pump, andthe angle of the transmission shaft ranges from 2 degrees to 4 degrees, so that stable and efficient transmission of the turbine engine is guaranteed, and a fault occurrence rate is reduced; a lubricating system driven by an auxiliary power system guarantees that the turbine engine, the reduction box and the plunger pump work under a proper environment; dual lubricating systems guarantee that theplunger pump realizes continuous operation under power of 5000 HP or higher; and the technical means finally can meet continuous large-power operation requirements of the fracturing equipment.

A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.

The present invention relates to a process for lubricating an aircraft engine, and preferably a turboreactor engine, comprising at least one shaft (2), in which the pressurization of oil taken from a reservoir (3), the distribution of the oil via a downstream circuit (5) to elements (6) of said engine, and the return of the oil via an upstream circuit (7) to the reservoir (3) are ensured by means of a pump (1, 15, 17), the rotational speed of said pump (1, 15, 17) being variable and adjustable, characterized in that this rotational speed of said pump (1, 15, 17) is preferably regulated by a predetermined law in order to adapt to the actual lubrication needs of said engine.

A heat exchange system for use in operating equipment having a plurality of subsystems in each of which a common working fluid is utilized to provide selected operations in that subsystem with a reservoir containing at least some of the common working fluid and has both a supply system and a return system connected between the reservoir and each of the plurality of subsystems through which any common working fluid in the reservoir can be conveyed. An airstream heat exchanger is provided connected in one of the supply and return systems so as to have the common working fluid conveyed therethrough cooled at selectively variable rates in the airstreams passing thereby during at least some such uses of the operating equipment.

An electric assisted turbocharger has an electric motor with a stator and a rotor that is coupled to a turbocharger shaft carried by a bearing assembly. The stator has a left-hand winding and a right hand-winding each projecting axially outwardly therefrom. The winds each extend a different distance radially along the motor (and are thus asymmetrical with respect to one another), thereby forming a radial gap along an axial end of the stator. The so-formed stator is disposed within a motor housing and together, the stator and motor housing, facilitate placement center housing axial end therein to minimize turbocharger axial length. The rotor is configured to prevent migration of oil into the motor housing, to improve dynamic balance, and comprises an integral thrust washer for placement against the bearing assembly.

The use of anti-friction ball bearings in a unique arrangement does not require the use of lubricating oil from the internal combustion engine lubricating system and permits close coupling of the bearings and a compact turbocharger. A turbocharger bearing housing forms a coolant jacket with an inner bearing engaging portion that has two bearing engagement surfaces engaged with the outer races of two anti-friction bearings whose inner races carry rotating shaft, turbine and compressor of the turbocharger. The anti-friction bearings are, preferably, angular contact ball bearings, and the two bearing engagement surfaces of the bearing housing are closely spaced, providing a turbocharger shaft of minimal length and substantially reducing the thermal expansion of the shaft. The coolant jacket protects the anti-friction bearings from exposure to the extreme heat of the exhaust gas driven turbine, notwithstanding their increased proximity due to the shortened turbocharger shaft. In addition, an external motor-generator may be carried by the compact turbocharger, and its motor may be connected to the turbocharger rotor assembly by a permanent, solid connector and stay connected throughout the entire operating range of the turbocharger. In such assembly, the electronic motor-generator control is mounted on the motor housing and energizes the motor from battery power during the engine acceleration period up to approximately the torque peak speed; thereafter, the control changes to a generator mode when excess energy is available in the engine exhaust gas.

A gas turbine including at least one compressor, one combustion chamber, and at least one turbine including at least one rotor and at least one generator coupled to the at least one rotor is provided. The at least one turbine is coupled to the at least one compressor. Once the gas turbine is shut down, the at least one generator can be used as a motor in order to drive the at least one rotor for a predetermined time period following shutdown of the gas turbine and thereby effect a uniform cooling of the rotor. A method of operating a gas turbine is also provided.

A thermal management system for a gas turbine powerplant with an engine oil line and an engine fuel line incorporates a heat transfer control module that includes a reversible heat pump with a heat pump compressor for circulating working fluid in forward and reverse directions through a working fluid line of the heat pump. The heat control module also includes a first heat exchanger having a heat exchange path for the working fluid between the compressor and a heat pump expansion valve and another heat exchange path for the engine oil. A second heat exchanger has a heat exchange path for the working fluid between the compressor and the expansion valve and another heat exchange path for the engine fuel. The heat pump can be operated in forward or reverse directions depending on whether heat is to be transferred from the engine oil or the fuel to the heat pump working fluid. In another embodiment an engine oil reservoir located between the first heat exchanger and the engine collects the oil before it is introduced to the engine and thus acts as a heat capacitor for the system.