14 results about "Turboprop" patented technology

The application discloses a mounting rack for turbo-prop engine shaft table test, which comprises a chassis assembly, a fixed main mounting section support, a stringing main mounting section support and two groups of auxiliary mounting section supports vertically arranged on the chassis assembly. The fixed main mounting section support and the stringing main mounting section support are used for being connected with two main mounting sections on the front end of the engine respectively, and the stringing main mounting section support is arranged along the radial direction of the engine to compensate the thermal expansion in the radial direction of the front end of the engine. The two groups of auxiliary mounting section supports are used for being connected with two auxiliary mounting sections on the middle and rear end of the engine respectively, and are arranged along the axial direction, the radial direction and the vertical direction of the engine to compensate the thermal expansion in the axial direction and the radial direction of the engine. The mounting rack can compensate the thermal expansion in the axial direction and the radial direction of the engine, so as to eliminate the additional load caused by the four supporting points of the engine not being on the same plane and shield the resonance frequency generated by the test bench and the engine.

A system (34) for controlling the pitch setting of a propeller blade (10) of a turbine engine of an aircraft is disclosed, characterized in that it comprises: - a blade (10) comprising a blade (12) connected to a root (14); - a cup (58) comprising an annular wall (58a) extending around a pitch axis (A) of the blade (10) and a lower axial end closed by a bottom wall (58b); - a fixing ring (52) extending around the root (14) and located inside the cup (58); the system further comprises a safety element (110, 110') ensuring the retention of the root (14) with the cup (58), said at least one safety element (110, 110') having a substantially elongated shape and passing through an aligned hole (112, 114, 126) in the bottom wall (58b) of the cup (58) and in the free end (28) of the root (14).

The application discloses a middle gear spiral combination for a reducer and a turbofan engine, which comprises a gear shaft with a pinion, a left shaft neck and a right shaft neck, and a large gear cooperating with the pinion to reduce transmission. The large gear and the pinion are both spiral gears, and the pitch circle diameter of the large gear is larger than that of the pinion. The middle gear spiral combination further comprises a connecting adjustment structure, the large gear is screwed on the outer circle of the gear shaft through the connecting adjustment structure, and is positioned between the pinion and the right shaft neck. The "Y" shaped reducer of the application can adjust the angle of the middle gear spiral combination, so that all the transmission tooth surfaces can be normally engaged without interference, and the effective transmission of power is facilitated. The "Y" shaped transmission scheme of the application divides the power flow into two parts, the radial pressure of the tooth surface is reduced to one half, the directions of the pressure vectors of the tooth surface are different, the vector sum is smaller than the sum of the values, the bearing life is prolonged, and the gear strength margin of the engine is improved.

The invention relates to a sub-compartment of an aircraft nacelle intended to accommodate a turboprop engine, the sub-compartment (1) comprising at least one fastening plate (2) and at least three lateral walls (3), the at least one fastening plate (2) comprising at least one electric circuit and at least one cooling circuit, and also at least one piece of electrical equipment mechanically fastened to the fastening plate (2) and connected to the electric circuit and to the cooling circuit of the fastening plate (2) to which it is fastened, the sub-compartment (1) furthermore comprising a ventilation system (5) comprising means (5a) for moving air connected at the inlet to a fresh-air suction mouth (5b), in order to admit fresh air into the sub-compartment (1) to cool the at least one piece of electrical equipment.

A land vehicle (12) for launching a UAV (14) with a wingspan of more than 2 metres, equipped with one or more turbojet or turboprop engines (16), is provided with a catapult system (26) for the UAV (14), comprising a launch ramp (28) and a mobile assembly (44) for supporting the UAV (14). The mobile assembly is guided by the launch ramp (28) in a launch direction (100) over a length of more than 6 metres, and preferably more than 8 metres. The catapult system (26) comprises at least one linear motor (46) comprising an inductor (48) arranged along the linear path and an armature (50) arranged on the mobile assembly (44) and at least one electrical energy accumulator with one or more supercapacitors (58) for supplying power to the linear motor (46).

De-icing method in a de-icing system (1) of a turboprop (100) comprising a fixed part (2) including an inverter (4) and an anti-icing control unit (7), a rotating part (3) including a rotary control unit (5) and a heating mat (9), and a rotary transformer (8) between the fixed and rotating parts, the method comprising upstream data transfers from the rotary control unit to the anti-icing control unit and downstream data transfers from the anti-icing control unit to the rotary control unit, wherein the method includes encoding steps: downstream data into frequency modulations of a supply voltage provided by the inverter around a predetermined nominal frequency; and upstream data into predetermined series of changes in an electrical power consumed by the rotary control unit.Figure for the abbreviation: [Fig.1].

A hybrid turboprop for an aircraft, including a gas generator carried by a generator shaft, a free turbine carried by a turbine shaft and driven in rotation by a gas stream generated by the gas generator, the turbine shaft being engaged with a main rotor via a transmission unit including a first free wheel oriented such that the main rotor cannot drive the free turbine, a reversible electric machine engaged with the main rotor via the transmission unit to drive the main rotor during electric or hybrid operation, the turboprop including a single oil pump engaged with the transmission unit so as to be selectively driven by the turbine shaft or by the electric machine depending on the operating mode.

An exhaust assembly for a turboprop engine, the assembly having: a primary exhaust nozzle disposed at an aft end of an engine core of the turboprop engine; a secondary exhaust nozzle extending aft from the primary exhaust nozzle to an aft end of the secondary exhaust nozzle, a movable panel disposed in the aft end of the secondary exhaust nozzle and movable to decrease an area of the secondary exhaust nozzle.

A sub-compartment of an aircraft nacelle intended to house a turboprop engine, said sub-compartment (1) comprising at least one mounting plate (2) and at least three side walls (3), the at least one mounting plate (2) comprising at least one electrical circuit and at least one cooling circuit, as well as at least one electrical component mechanically fixed to the mounting plate (2) and connected to the electrical circuit and the cooling circuit of the mounting plate (2) to which it is fixed, the sub-compartment (1) further comprising a ventilation system (5) comprising means for moving air (5a) connected at the inlet to a fresh air intake (5b), in order to admit fresh air into the sub-compartment (1) to cool the at least one electrical component. Figure for the abbreviation: [Fig 1]

The application discloses an aero turboprop engine lubricating oil system, which comprises a lubricating oil pressurizing device, an oil-gas separating device, a lubricating oil returning device, a lubricating oil filtering device, a lubricating oil monitoring device and connecting pipes connecting the devices; the lubricating oil pressurizing device comprises a main lubricating oil pump, an auxiliary lubricating oil pump and a torque measuring pump; the oil-gas separating device comprises an air inlet tank, an air separator and an oil mist separator; the lubricating oil returning device comprises a lubricating oil tank, a lubricating oil radiator, a middle and rear bearing oil pump, a transmission box oil pump and a direct current electric lubricating oil pump; the lubricating oil filtering device comprises a lubricating oil filter and a middle and rear bearing oil returning filter; and the lubricating oil monitoring device comprises a temperature metal chip signaler and a magnetic chip detection signaler. The application provides suitable lubricating oil pressure and oil quantity, improves the lubrication and heat dissipation of the friction surface of the internal parts of the engine and improves the use reliability of the engine.

The application discloses a test method for emergency pull function of a turboprop engine, and comprises the following steps: firstly, determining test target requirements of the emergency pull function of the turboprop engine; secondly, determining a test scheme of the emergency pull function of the turboprop engine; and finally, performing verification test of the emergency pull function of the turboprop engine. The test method can solve the problem that the turboprop engine is required to automatically switch to the emergency take-off function after single engine failure according to the general requirements of the turboprop engine development, and provides a new idea for other engines, greatly improves the test technical level of the engine emergency pull function, and greatly reduces the test risk by adopting the step-by-step verification and layer-by-layer progressive verification idea, so that the safety is higher, the application range is wider, and the success rate of the test is ensured.

The application discloses a kind of penetrant and its preparation nickel-based superalloy piece aluminizing layer process, penetrant includes the raw material of following mass fraction proportioning: aluminum powder 18%~22%, ammonium chloride 0.5%~1.2%, the rest is calcined alumina.The application uses new raw material and proportioning to prepare penetrant, and the aluminum content of penetrant is moderate, can well meet the requirement of infiltration layer;Optimized heating and holding parameters in aluminizing process play a crucial role on the performance of infiltration layer, ensure that the prepared nickel-based superalloy piece aluminizing layer depth, organization can meet the design requirement, especially for the hollow turbine blade aluminizing on aero-engine, its infiltration layer oxidation resistance, high-temperature gas corrosion resistance, neutral salt spray corrosion resistance can meet the requirements of hollow gas turbine blade oxidation resistance, high-temperature gas corrosion resistance of turboshaft, turboprop engine;The prepared penetrant of the application can be reused, and can ensure that the depth of infiltration layer, infiltration layer organization and aluminum content are within the qualified range.

Twin-rotor synchroopter helicopters, for combat and reconnaissance, two-seat, light, medium, or heavy, using the control surface for piloting and also for changing the position of the engine block on the fuselage, between the cabin 1 with vertical scanning radar 2, and the tail assembly with a ducted turboprop engine 5 and an air-to-air or surface-to-air missile launcher 4. The panoramic radar 3 is in flight position. Two motorcycles 8 are suspended below the central engine block when the main landing gear is in the lowered position 6 and the landing gear bay 7 is open.