1705results about "Turbine/propulsion air intakes" patented technology

The invention discloses a turbine fracturing semitrailer. The turbine fracturing semitrailer comprises a semitrailer body, a turbine engine, a reduction gearbox, a transmission mechanism and a plungerpump; the turbine engine, the reduction gearbox, the transmission mechanism and the plunger pump are arranged on the semitrailer body, the output end of the turbine engine is connected with the reduction gearbox, and the reduction gearbox is connected with the plunger pump through the transmission mechanism in a transmission mode. The turbine fracturing semitrailer has the beneficial effects thatthrough linear connection of the turbine engine, the reduction gearbox, the transmission mechanism and the plunger pump in the power-transmission direction, excessive transmission loss can be avoided, and efficient transmission performance is guaranteed; and the whole semitrailer is small in size, light in weight, low in the use cost, and low in failure risks.

The invention discloses an intake and exhaust system of a turbine engine. The intake and exhaust system of the turbine engine comprises an intake system and an exhaust system, wherein the intake system is connected with an intake port of the turbine engine, the exhaust system is connected with an exhaust port of the turbine engine, the intake system comprises an intake filter and an intake pipeline, the intake filter is connected with the intake pipeline, the intake filter adopts a V-shaped structure, and a rain shielding cap is arranged at the exhaust tail end of the exhaust system. The intake and exhaust system of the turbine engine has the beneficial effects that the air inlet area is large, the air inlet flow speed is lower, the service life of an air filter is long, the rain shieldingcap additionally arranged at the exhaust port avoids the rainwater deposition in an exhaust silencer, the condition that rainwater possibly flows backwards is avoided and damages the turbine engine,and an opening of the rain shielding cap is away from the intake port, so that exhausted waste gas is prevented from being sucked by the intake port, and the quality of inlet air is ensured.

An inlet bleed heat and power augmentation system utilizing a bi-directional and common piping arrangement is disclosed. The piping arrangement includes a plurality of feed tubes arranged to communicate either steam to a compressor discharge plenum or compressed air from the compressor discharge plenum. Various embodiments of the invention are discussed including operation methods.

Apparatus and method for detecting incipient lean blowoff conditions in a lean premixed combustion nozzle of a gas turbine. A sensor near the flame detects the concentration of hydrocarbon ions and / or electrons produced by combustion and the concentration monitored as a function of time are used to indicate incipient lean blowoff conditions.

Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved through methods or systems that ensure delivery of a consistent mass flow rate of oxidant to the combustion chamber.

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

Noise reduction sandwich panel, notably for an aircraft turbojet engine.In order to produce a noise reduction sandwich panel having a structure with two degrees of freedom, inserted separative components (20) are placed into the hexagonal cells (16) of the unique waffle core of the panel. More specifically, the separative components (20) have an substantially circular external peripheral edge, which allows them to be easily assembled, in spite of the deformations of the walls (18) of the cells (16) due to manufacturing tolerances and to the optional forming of the waffle core. Advantageously, several separative components (20) are supported by a same positioning unit (22), which then allows relative displacement between the separative components.

An aircraft engine assembly is provided that is adapted to reduce noise produced by an engine included in the engine assembly. The engine assembly includes a nacelle having an inlet section and a main section that is houses the engine and fan assembly associated with the engine. The inlet section is coupled to the main section at a main bulkhead junction between the inlet section and the main section. A one piece annular acoustic panel is located within a recess in an internal wall of the nacelle. The annular acoustic panel extends from a forward portion of the inlet section to a forward portion of the main section such that the bulkhead is covered by the annular acoustic panel.

A high drag vortex generator for inhibiting the formation of boundary layer gas flow is mounted in a duct having a strong adverse pressure gradient with high speed gas flow over a primary aerodynamic. The vortex generator includes a mounting for supporting the high drag vortex generator at a spatial interval in the high speed gas flow above the primary aerodynamic surface. The high drag vortex generator is supported from the mounting and extends from the mounting in the high speed gas flow less than the full distance to the primary aerodynamic surface. Each high drag vortex generator includes first and second vanes. The first and second vanes have flow confining components at substantial right angles to one another. The vanes flow confining components deflect fluid flow towards and / or away from the primary aerodynamic surface inhibiting boundary layer formation downstream of the vortex generator.

A method operable to improve pressure recovery and / or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and / or distortion of the inlet when the particular engine conditions.

An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) contained within an aircraft housing is provided. The inlet assembly includes an inlet duct, an actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage through which APU noise propagates. The actuator is disposed at least partially within the inlet duct. The door coupled to the actuator. The actuator is also configured to selectively rotate the door between at least a first position, in which at least a portion of the door deflects APU noise in a first direction, and a second position, in which at least a portion of the door deflects the APU noise in a second direction.

The invention provides an internal waverider-derived hypersonic inlet based on arbitrary shockwave shape and a design method thereof. The structure of the internal waverider-derived hypersonic inlet comprises an inlet contraction section and an inlet insulation section; wherein the inlet contracting section is inward contracted in three-dimension; hypersonic velocity incoming flow forms irregular initial incident three-dimensional shockwave at the inlet; and the shockwave closes the three-dimensional inlet surface completely. The design method comprises the following steps: an internally contracted axisymmetric basic flow field used as a base is formed by the combination of ICFA flow field and partial Buesemann flow field; and after shapes of shockwave sections with different centers of curvature and directions of curvature are appointed, flown line tracing of the basic flow field with different centers and different radial positions is carried out on a plane in each circle of the hypersonic inlet to obtain the internal waverider-derived hypersonic inlet based on arbitrary shockwave shape. The internal waverider-derived hypersonic inlet and the method have the advantages of ensuring that the hypersonic inlet captures the incoming flow in full flow, increasing thrust force of an engine while reducing overflow resistance, improving pneumatic performance of an outlet of the hypersonic inlet, reducing windward external resistance of the hypersonic inlet, and improving starting performance of low-mach number of the hypersonic inlet.