WO2015069147A1

WO2015069147A1 - Airplane and gas turbine power plant with a separate wing-root engine

Info

Publication number: WO2015069147A1
Application number: PCT/RU2014/000839
Authority: WO
Inventors: Владимир Тарасович ШВЕДОВ
Original assignee: Владимир Тарасович ШВЕДОВ
Priority date: 2013-11-07
Filing date: 2014-11-06
Publication date: 2015-05-14
Also published as: RU2013149503A; RU2567914C2

Abstract

A power plant having a separate wing-root engine which comprises an outer cowling, a compressor, a combustion chamber and a turbine that drives the compressor, and having propulsion devices which are situated separately from the wing-root gas turbine engine. A part of the air processed by the compressor is supplied to the combustion chamber and to the turbine and is used to drive the compressor, and another part of the remaining high-pressure air enters a delivery conduit of the propulsion devices. The power plant comprises one or more vortex pump-jets in the form of streamlined nacelles which contain a flow duct consisting of an inlet convergent portion, a divergent portion, a vortex chamber and an outlet device, connected in succession. The nacelle is provided with an inlet duct, which is connected to the delivery conduit, and outlet nozzles, which communicate with the inlet duct and are arranged in the outlet part of the divergent portion, around the circumference thereof, at an angle to the axis of the nacelle such that the jets exiting the outlet nozzles generate a vortex in the stream of air passing through the flow duct. The result is improved performance, reduced mass and a simplified design of the power plant, and reduced fuel consumption on the part of the airplane.

Description

AIRCRAFT AND GAS TURBINE INSTALLATION

WITH DIVIDED ROOT ENGINE

The field of technology.

The invention relates to mechanics, to engines, and more particularly, to jet engines without gas turbines, and can be used in the design of propulsors for vehicles moving in air, water and other fluids.

The invention may find application in aviation, water, and other modes of transport. .

The prior art.

Double-circuit jet engines (turbojet engines) are known in which the thrust is created in two circuits: a gas turbine and a fan (second) circuit. If there is no afterburner in the secondary circuit, the creation of draft in it includes: suction of air from the environment in the input device, its compression by a fan (or compressor), pumping of the second circuit through the air duct, and the implementation of the draft by expanding the flow in the output nozzle. (See A.L. Klyachkin. Theory of jet engines.

"Engineering", M, 1969, p. 17-19). A fan circuit usually contains an input device (otherwise common with a gas turbine circuit), a compressor (fan), and an exhaust nozzle.

The fan circuit also contains one or more crowns of straightening vanes located behind the fan and designed to straighten the flow swirling on the fan. (See V.A. Shulgin. Dual-circuit turbofan engines of low-noise aircraft., P. 150.). The disadvantage of turbofan engines and, in particular, the fan circuit, is the low efficiency (efficiency). So for the fan circuit there are losses of air flow created by the compressor on the turbine, mechanical transmission from the turbine to the fan (including the gearbox), the fan itself, the rectifying device, which leads to efficiency equal to 0.3-0.4. To create great traction, low efficiency is offset by high fuel consumption.

Known gas turbine installation with a dedicated root engine, contains at least one root gas turbine engine and the movers located separately from it. The root gas turbine engine comprises an external fairing, a compressor, a combustion chamber, and a turbine driving the compressor via a shaft.

Otherwise, such a dedicated root engine uses components and parts of known design to ensure its operation. In this case, part of the air produced by the compressor is supplied to the combustion chamber and turbine and is used to drive the compressor. Another part of the remaining high-pressure air enters the pipeline to power the propulsors. The installation has at least one mover located separately from the specified root engine and provided with high pressure air from the specified root engine for its operation, and at least one controlled mover for controlling the aircraft, containing an air turbine located separately from the specified root engine and driven high-pressure air from said root engine; and a controlled fan driven by said air turbine. The mover, located separately from the specified root engine, has a fan driven by its turbine, operating directly from compressed air taken from the root engine, or may be equipped with an additional own combustion chamber to drive the turbine.

Such a gas turbine installation can be used on an aircraft with propulsion devices located on the fuselage, or on a wing, in particular a vertical take-off apparatus, for its vertical take-off or landing. (See European patent EP 1 331 378 A2, F02C 1/02, 2003). Aircraft using a gas turbine are also presented there.

According to the inventors, this embodiment of a turbofan engine with dedicated propulsion units can reduce the noise generated by the installation. In addition, the convenience and simplicity of the layout of propulsion systems for aircraft for various purposes is provided.

However, such a gas turbine installation has an increased mass of the structure and, in addition, a lower efficiency due to additional losses on external fans with turbines, in pipelines. Therefore, the use of such gas turbine units in passenger and transport aircraft is not practical.

Known vortex ejector propulsion (FEA) according to the patent of R.F. Ng 2465481, IPC F02k 7/10, 2012. The vortex mover is made in the form of a streamlined hollow nacelle, acting as a body, the inner surface of the nacelle is an air path, consisting of communicating in series located input device, made in the form of a confuser, a diffuser, a vortex chamber and an output device, in addition, the nacelle is equipped with a device for supplying compressed air inside the air path, made in the form of nozzles communicating with a source of compressed air located in front of the nacelle along the entire perimeter of the cross section and directed at an angle to the axis of the air path equal to 10-60 ° so that it swirls the air in it in one direction, creating a vortex. The mover can be used to drive any vehicle unit, or as a pump for pumping fluids. To do this, it is necessary to equip it with a gas generator (for operation in the atmosphere).

At present, the layout of foreign economic activity with turbo-gas generators is unknown and its use in aviation is not known.

Disclosure of the invention.

The objective of the invention is to develop such a design of a gas turbine installation having an increased efficiency.

Moreover, a gas turbine installation should have less weight and a simplified design, and an airplane using it should have a reduced fuel consumption.

This object is achieved in that a gas turbine installation with a dedicated root engine, comprising at least one root gas turbine engine, comprising an external fairing, a compressor, a combustion chamber and a turbine driving the compressor, and propulsion devices located separately from the root gas turbine engine, air produced the compressor, is fed into the combustion chamber and the turbine and used to drive the compressor, and the other part of the remaining high-pressure air enters the power supply pipeline of the propulsion devices, contains one or more vortex ejector propulsors made in the form of streamlined nacelles containing a flow path, consisting of an input confuser, a diffuser, a vortex chamber, and an output device, while the nacelle is equipped with an inlet pipe connected to the power supply pipe, and final year at the nozzles communicating with the inlet and disposed in the outlet portion of the diffuser along its circumference at an angle to the axis of the nacelle so that jets issuing from them would create a vortex in the flow path passing through the air stream.

In addition, each of the propulsors is made with a vortex chamber, the inner surface of which is made in the form of a truncated cone with a large base connected with the outlet cross section of the diffuser, and a smaller base constituting the exhaust hole.

At the same time, the output devices of the propulsors are made in the form of an additional diffuser and are equipped with rectifying devices.

In an airplane, propulsion devices are made in the form of vortex ejector propulsors made in the form of streamlined nacelles containing a flow path consisting of an inlet confuser, a diffuser, a vortex chamber and an output device connected in series, while the nacelle is equipped with an inlet pipe connected to the power supply pipe, and exhaust nozzles communicating with the inlet pipe and located in the outlet part of the diffuser along its circumference at an angle to the axis of the nacelle such so that the jets emerging from them would create a vortex in the air flow passing through the propulsion duct; the supply pipeline is made in the form of a common main pipeline connected with the inlet nozzles of the vortex ejector engines and with the annular samplers of each of the engines using nozzles equipped with check valves to prevent the supply of compressed air to the failed engine; dedicated root engines are mounted on pylons under the wing, and eddy ejector propulsors are installed on the upper surface of the wing, while the power supply pipe is installed in the front compartment of the wing.

Such a gas turbine installation will improve the fuel efficiency of vehicles using it.

The list of figures in the drawings.

The invention is illustrated by drawings, in which:

-Fig.1 - shows a diagram of a gas turbine installation, made in accordance with the invention and using two vortex propulsors, in longitudinal section along the axes of the engine and propulsors;

- FIG. 2 - shows a vortex ejector propulsion in longitudinal section along the axis of symmetry;

- FIG. 3 - shows the general view of the aircraft (in plan) using gas turbine units with a dedicated root engine;

- FIG. 4 shows a section A-A of FIG. 3. The implementation of the invention.

The invention is implemented as follows.

A gas turbine installation with a dedicated root engine contains at least one root gas turbine engine 1 and movers 9 and 10 located separately from it (see Figure 1). The root gas turbine engine 1 contains an external cowling 3, a compressor 2, a combustion chamber 6 and a turbine 7 driving the compressor 2 by means of a shaft 4. Moreover, the root gas turbine engine is made according to the known construction of a gas turbine engine of the first circuit of a double-circuit gas turbine engine (DTRD), except that there is no second circuit in it (fan, casing, rectifier, gearbox, mechanical transmission that connects the turbine to the fan). In addition, the output of the compressor 2 is connected to the turbine 7 and is made with an annular sampler 5 for taking air for propulsors so that part of the air produced by the compressor is supplied to the combustion chamber, the turbine and used to drive the compressor, and the other part of the remaining high pressure air enters the power supply pipe 8 of the propulsion devices,

In all other respects, the root gas turbine engine is equipped with units and equipment of known designs necessary for its effective functioning.

A gas turbine installation contains one or more vortex ejector propulsors that play the role of a second DTRD circuit. Vortex ejector propulsors are made (see Fig. 2) in the form of streamlined nacelles 1 1. containing a flow path 20, consisting of an inlet confuser 13 connected in series with each other, the diffuser 14, the vortex chamber 15 and the output device 16. In this case, the nacelle is equipped with an inlet pipe 17 connected to the supply pipe 8, and exhaust nozzles 19. The exhaust nozzles are made communicating with the inlet pipe 17 and located in the outlet of the diffuser around its circumference at an angle 22 to the axis of the nacelle so that the jets leaving them create a vortex 21 in the air flow passing through the flow path. The connection of the nozzles 19 with the outlet pipe can be performed using the discharge chamber 18, made in the Hondola annular around the flow path.

It is advisable that each of the propulsors was made with a vortex chamber, the inner surface of which is conical, in the form of a truncated cone, with a large base associated with the outlet cross section of the diffuser and a smaller base constituting the exhaust opening. The taper angle is 6-12 °.

To improve traction characteristics, each of the propulsors can be made with a vortex chamber, the inner surface of which is made in the form of a truncated cone with a large base connected with the outlet cross section of the diffuser, and a smaller base connected with the output device made in the form of an additional diffuser.

In addition, the output devices of the propulsors can be equipped with rectifying devices made of known designs, for example in the form of guide radial blades.

The design of the vortex ejector propulsion can be made of various known solutions. For example, constructively the mover can be made comprising a housing, including a discharge chamber with insertion nozzles, a front part with an input device and a tail part with a vortex chamber and an output device mounted on shelves made in front and rear of the housing.

At the same time, the body can be made of metal from aluminum or magnesium casting, and the front and rear parts can be made of composite materials.

Works gas turbine as follows.

When the root gas turbine engine 1 is running, part of the air produced by the compressor 2 is supplied to the combustion chamber 6, where it is mixed with the combustion products and enters the turbine 7, bringing it into action. The turbine is used to drive a compressor that produces the required amount of compressed air.

Another part of the remaining high-pressure air enters the annular sampler 5 and then into the power supply pipe 8 of the propulsion devices 9 and 10. High-pressure air entering the discharge chamber 18 is discharged in the form of high-energy jets through the nozzles 19 into the flow path 20 at an angle of 22 to the axis nacelles so that the jets leaving them create a vortex 21 in the passing air stream 23. The vortex 21 created in the air stream 23 acts on it, turning the stream into a vortex, which in turn creates a rarefaction at the entrance to the mover, contributing to an increase in air flow through the mover. The accelerated air flow together with the ejection air from the nozzles creates increased draft and power due to environmental energy. Aircraft using gas turbine units with a dedicated root engine.

Aircraft 30 (see Fig. 3) includes a fuselage 33, half wings 31 and 32, tail unit 35 with vertical and horizontal surfaces. The aircraft also contains a marching power plant consisting of left 37 and right 38 dedicated root engines mounted on pylons under the wing. Moreover, each root gas turbine engine is made according to the known design of the gas turbine engine of the first circuit of a double-circuit gas turbine engine (DTRD), except that there is no second circuit in it (fan, casing, rectifier, gearbox, mechanical transmission that connects the turbine to the fan). In all other respects, the root gas turbine engine is equipped with units and equipment of known designs necessary for its effective functioning.

In addition, the compressor output of each engine is made with an annular sampler 49 (Figure 4) for air extraction for propulsors so that part of the air produced by the compressor is supplied to the combustion chamber, turbine and used to drive the compressor, and the other part of the remaining air is high pressure enters the pipeline 43 installed in the front compartment of the wing floor and center section for. power propulsion devices. For this, the annular sampler of each engine is connected to a pipe 45 (46 for the right engine) installed in the pylon, the other end connected to the pipe 43. Thus, compressed air from both engines 37, 38 enters the pipe 43. Each of the pipes 45, 46 is equipped with a check valve (not shown in the diagram) to prevent compressed air from flowing into the failed engine. From the pipeline 43 compressed air enters the discharge chamber 51 of each propulsion device connected by its inlet pipe to the pipeline using an adapter.

Movers 39,40, 41 and 42 are mounted on the upper surface of the wing using pylons 47.

The above example implementation of the invention is not the only one possible. The simplicity of the design of vortex ejector propulsors, the simplicity of energy carrier delivery (compressed air), the ability to install them on any surface, on any unit, represents a wide selection of aircraft designs.

The following promising layouts of power plants are possible.

1. "Reverse circuit" - when the root dedicated gas turbine engines are installed in a known manner on the wing, and the vortex ejector engines are located on the lower surface of the wing. At the same time, all structural units, communications remain the same.

This embodiment of power plants allows you to increase the flight safety of the aircraft in connection with less damage to the engines, reduce the height of the landing gear.

2. Root isolated gas turbine engines are installed in a known manner inside the fuselage (in particular in its rear part), providing air flow to them using air intakes, and vortex ejector engines are located on its surface, or on pylons or special surfaces, plumage. At the same time, all structural units, communications remain the same. Otherwise, the aircraft is equipped with well-known systems and equipment that ensure its functioning.

When the engines are running, high-pressure compressed air enters the propulsion chambers, from where it is ejected through the nozzles in the form of high-energy jets into the flow path at an angle to the axis of the nacelle so that the jets leaving them create a vortex in the passing air stream. A vortex created in the air flow acts on it, turning the flow into a vortex, which in turn creates a vacuum at the inlet of the propulsion, contributing to an increase in air flow through the propulsion. The accelerated air flow together with the ejection air from the nozzles creates increased draft and power due to environmental energy.

In addition, the accelerated air flow from the propulsors creates increased circulation on the wing, which leads to an increase in the load-bearing properties of the wing. Moreover, since the air flow from the propulsors is a vortex, this contributes to an increase in this effect.

It is advisable that the direction of rotation of the air stream (jets) from two movers located on the same wing is multidirectional (which is determined by the design of the mover, namely, the direction of deviation of the axes of the nozzles, creating a clockwise or counterclockwise rotation) .. Moreover, when choosing the direction of rotation , creating a direction of influence of the vortices (jets) on top of each other, sticking of the jets to the wing surface and increase in traction will be prevented. In the opposite direction (down), the jets will contribute to adhesion to the wing surface and create an increased lifting force of the wing. When using propulsors with output devices containing rectifying devices, the above effects disappear, but maximum traction is provided.

Industrial applicability.

A gas turbine plant with a dedicated root engine and an airplane using such a plant as vortex ejector engines do not require new unknown technologies for their production and can be produced using existing ones.

Moreover, the use of such installations in aviation, in particular on passenger aircraft, allows to obtain a number of positive effects:

- increased flight safety by reducing the likelihood of engine damage in flight by birds, and on the ground from stones falling into the air intakes;

- reduced fuel consumption due to increased efficiency in vortex ejector propulsors, which contributes to increased fuel efficiency;

- simplification and reduction of the mass of gas turbine plants, simplification and reduction of the cost of their maintenance,

- reduced noise on the ground and in the cockpit;

- increase environmental friendliness by reducing emissions.

Claims

Claim.

1. A gas turbine installation with a dedicated root engine, comprising at least one dedicated root gas turbine engine, comprising an external cowling, a compressor, a combustion chamber and a turbine driving the compressor, and propulsion devices located separately from the dedicated root gas turbine engine, wherein the compressor output of each engine made with an annular sampler for air selection for propulsors in such a way that part of the air produced by the compressor is supplied to the combustion chamber and urbine and is used to drive the compressor, and the other part of the remaining high-pressure air enters the power supply pipeline of propulsion devices, characterized in that it contains one or more vortex ejector propulsors made in the form of streamlined nacelles containing a flow path consisting of an inlet confuser connected in series , a diffuser, a vortex chamber and an output device, while the nacelle is equipped with an inlet pipe connected to the power supply pipe and exhaust nozzles communicating with the inlet pipe and located in the outlet part of the diffuser along its circumference at an angle to the axis of the nacelle so that the jets leaving them create a vortex in the air flow passing through the flow path.

2. A gas turbine installation with a dedicated root engine according to claim 1, characterized in that each of the propulsors is made with a vortex chamber, the inner surface of which is made in the form of a truncated cone with a large base associated with the outlet cross section of the diffuser and a smaller base constituting the exhaust hole .

3. A gas turbine installation with a dedicated root engine according to claim 1, characterized in that each of the propellers is made with a vortex chamber, the inner surface of which is made in the form of a truncated cone with a large base associated with the outlet cross section of the diffuser, and a smaller base associated with the outlet a device made in the form of an additional diffuser.

4. A gas turbine installation with a dedicated root engine according to claim 1, characterized in that the output devices of the propulsors are equipped with rectifying devices.

5. Aircraft containing the fuselage, half wings and tail with vertical and horizontal surfaces mounted on the fuselage, a marching gas turbine power plant, including at least two engines, each of which is made in the form of a dedicated root gas turbine engine containing an external fairing, compressor, chamber combustion and a turbine driving the compressor, and propulsion devices located separately from the allocated root gas turbine engine, wherein the compressor output of each engine The spruce is made with an annular sampler for air extraction for propulsors, so the part of the air produced by the compressor is supplied to the combustion chamber and turbine and used to drive the compressor, and the other part of the remaining high pressure air enters the power supply pipeline of the propulsion devices, and other systems and equipment, ensuring its operation, characterized in that the propulsion devices are made in the form of vortex ejector propulsors made in the form of streamlined nacelles containing flow th path, consisting of a series interconnected inlet confuser, diffuser, vortex chamber and output device, while the nacelle is equipped with an inlet pipe connected to the supply pipe, and exhaust nozzles communicating with the inlet pipe and located in the output part of the diffuser around its circumference at an angle to the axis of the nacelle in this way so that the jets emerging from them would create a vortex in the air flow passing through the propulsion duct.

6. The aircraft according to claim 5, characterized in that the supply pipe is made in the form of a common main pipe connected to the inlet nozzles of the vortex ejector engines and to the annular samplers of each of the engines using nozzles equipped with check valves preventing the supply of compressed air to the failed engine ;

7. Aircraft according to claim 5 or 6, characterized in that the allocated root engines are mounted on pylons under the wing, and eddy ejector engines are installed on the upper surface of the wing, while the power supply pipe is installed in the front compartment of the wing.