RU2780910C1 - Combined pulsating output device of a turbojet bypass engine - Google Patents

Abstract

FIELD: engine building.

SUBSTANCE: invention relates to the field of engine building and can be used to create jet thrust on aircraft and stationary power plants. The combined pulsating output device of a turbojet bypass gas turbine engine with separate outer and inner circuits contains a tapering sonic nozzle in the inner circuit, and a two-dimensional gas-dynamic resonator made in the form of a ring element with a a resonator cavity, the traction wall of which is made in the form of a torus dissected in cross section, while annular protrusions are formed on the outer and inner walls of the outer contour, forming an annular gap with the corresponding outer and inner edges of the resonator cavity of the two-dimensional gas-dynamic resonator.

EFFECT: invention provides an increase in thrust while maintaining the weight and dimensions of the turbofan engine.

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Description

The invention relates to the field of engine building and can be used to create jet thrust on aircraft and stationary power plants.

The design of a bypass turbojet engine (SU 117179 dated 01/01/1958) is known, in which the air is divided into two streams: an internal one, passing through a fan and a gas turbine, and an external one, passing only through a fan, which is rotated by a turbine located in the internal circuit. The outflow of the jet stream can either pass through two separate nozzles, or the gas flows behind the turbine are mixed in a special mixing chamber and flow out into the atmosphere through one common nozzle.

The disadvantage is that an increase in the thrust of the turbofan engine, while maintaining the traction and economic characteristics, leads to an increase in the overall mass characteristics of the engine.

The technical problem solved by the claimed invention is to increase efficiency.

The technical result is to increase the amount of thrust while maintaining the weight and dimensions of the turbofan engine.

The specified technical result is achieved in a combined pulsating output device of a turbojet bypass gas turbine engine with separate external and internal circuits, containing a tapering sonic nozzle in the internal circuit, and in the external circuit, in the region of the outlet section with a gap between the outer and inner walls of the outer circuit, a two-dimensional gas-dynamic resonator , made in the form of an annular element with a resonator cavity, the traction wall of which is made in the form of a torus dissected in cross section, while annular protrusions are formed on the outer and inner walls of the outer contour, forming an annular gap with the corresponding outer and inner edges of the resonator cavity of the two-dimensional gas-dynamic resonator.

The claimed invention is illustrated on graphic materials, where:

figure 1 shows a diagram of the output device of a turbofan without mixing flows (flows A in the outer circuit and B in the inner), which flow from separate nozzles. Flow A flows out through the annular nozzle of the two-dimensional gas-dynamic resonator (2). Stream B is expiring and converging sonic nozzle (1);

figure 2 shows the output device of a turbofan without mixing flows with an outer annular nozzle and an annular two-dimensional gas-dynamic resonator (GDR) (2) and a sonic tapering nozzle (1) (rear view);

figure 3 shows a diagram of the installation of a two-dimensional GDR in the external circuit of the turbofan without mixing flows. The GDR is located close to the cut of the outer wall of the outer contour casing. The inner and outer rings (3) are installed along the circumference of the body, which, together with the end walls of the two-dimensional GDR, form the upper I and lower II slots of the annular nozzle.

The combined pulsating output device (CPVU) is used for engines having a secondary circuit without a mixing chamber and used as part of the power plants of subsonic aircraft.

KPVU is an output device of a bypass gas turbine engine without a mixing chamber. The inner circuit uses a standard tapered sonic nozzle (1). In the outer contour of the engine, between its inner and outer walls, a two-dimensional GDR (2) is installed. The gas-dynamic resonator has the shape of a trough, which is a torus dissected in cross section, and is installed so that the end of the trough is at the cut of the outer contour of the output device (figure 1). By changing the distance between the rings and the ends of the resonator, the area of the annular nozzle is controlled, which determines the flow rate of the working fluid through the outer contour.

A two-dimensional GDR is installed at the exit of the annular nozzle of the external contour of the turbofan engine without mixing flows (Fig. 3). The annular walls 3 and the end walls of the two-dimensional GDR form the upper slot I and the lower slot II of the annular nozzle. The gas flow from the slots of the annular nozzle flows out perpendicular to the axis of the engine and, upon impact, a process of undamped pressure pulsation in the flow is organized. In the pulsating flow, an additional compression of the gas flow occurs, while the speed of the jet outflow from the annular nozzle increases and increases the thrust value by 10-15%.

The use of a two-dimensional GDR will allow, without increasing the mass and dimensions of the turbofan engine, to improve its specific parameters and traction and economic characteristics by 10-15%.

Claims (1)

Combined pulsating output device of a turbojet bypass engine with separate external and internal circuits, containing a tapering sonic nozzle in the internal circuit, and a two-dimensional gas-dynamic resonator made in the form of an annular element with a resonator cavity, the traction wall of which is made in the form of a torus dissected in cross section, while annular protrusions are formed on the outer and inner walls of the outer contour, forming an annular gap with the corresponding outer and inner edges of the resonator cavity of the two-dimensional gas-dynamic resonator.

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