CN105298683A - Throat deviating type pneumatic thrust vectoring nozzle with fuel supplementing and thrust augmenting functions and control method - Google Patents

Abstract

The invention discloses a throat offset type aerodynamic vector nozzle with the function of supplementary combustion and afterburner. The inner flow channel of the nozzle comprises in turn a converging section at the front of the throat, a throat, an expanding and converging section at the front of the second throat, and a second throat. The main body that realizes its post-combustion afterburning function is achieved by fuel nozzles arranged at the sharp point of a throat or by mixing fuel into the secondary flow injected near a throat and burning it downstream of a throat. By controlling the angle, speed, and flow of fuel injected by the fuel nozzle or controlling the ratio of fuel to air in the secondary flow and the size of the secondary flow, it is possible to control the vector angle of the nozzle and the area of the throat, and to achieve afterburning. It is of great significance to accelerate the flight in the air of the aircraft using the throat offset aerodynamic vectoring nozzle.

Description

Throat offset aerodynamic vectoring nozzle with afterburning afterburning function and its control method

technical field

The invention relates to the field of aircraft propulsion system design, in particular to a throat offset aerodynamic vectoring nozzle.

Background technique

With the development of science and technology, more and more aircraft are equipped with thrust vectoring aeroengines. For fighter jets and missiles, afterburning is not needed during conventional flight; when evading, intercepting, chasing, and maneuvering, it is inevitable to perform afterburning to increase the total temperature of the engine nozzle outlet. Total pressure to increase engine thrust for acceleration while maneuvering using thrust vectoring techniques. Therefore, a nozzle device with both thrust vectoring technology and afterburning afterburning technology is of great value for the realization of future aircraft.

At present, there are many separate designs for thrust vectoring nozzle and afterburning afterburner, but there are few designs that integrate the two together. Not to mention the difficulty and difficulty of the fusion design of the two, as far as the thrust vectoring nozzle is concerned, most designs remain on paper due to problems such as complex mechanical structure, bulkiness, poor reliability, and high cost, and rarely realize engineering applications.

Throat offset aerodynamic vectoring nozzles are divided into active and passive throat offset aerodynamic vectoring nozzles. It is a new type of thrust vectoring technology emerging in recent years. With its simple structure and light weight, it is popular growing in favor.

The structure of a typical throat offset aerodynamic vectoring nozzle is a double-throat type, in which the gas flowing in it sequentially flows through the converging section at the front of one throat, the first throat, and the expanding and converging section at the front of the second throat, and finally from Outflow from the second throat. Of course, there are also some other configurations of throat offset aerodynamic vectoring nozzles, which will not be described here.

The active throat offset pneumatic vectoring nozzle usually bleeds air from the engine compressor, turbine, intake or external atmosphere, and also has high-pressure gas cylinders, air pumps, etc. Angle, velocity, and flow injected into the main flow create disturbances that function as thrust vectors. The passive throat offset aerodynamic vectoring nozzle usually bleeds air from the outlet of the engine turbine, or divides the airflow entering the nozzle into several streams and injects one or several streams into the mainstream to generate disturbance, so as to obtain the vector effect.

Contents of the invention

Purpose of the invention: In order to overcome the deficiencies in the prior art, the present invention provides a throat offset aerodynamic vectoring nozzle with afterburning and afterburning functions, which is used to solve the problem that existing aircraft do not have aerodynamic thrust vectoring technology at the same time. And the technical problem of the nozzle of afterburner technology.

Technical scheme: in order to achieve the above object, the technical scheme adopted in the present invention is:

A throat offset aerodynamic vectoring nozzle with post-combustion afterburner function, a fuel inlet and an igniter are arranged in the throat offset aerodynamic vectoring nozzle, and the position of the fuel inlet is set before and after a throat , the distance from a throat is not more than 20% of a throat height, and the igniter is arranged at a position downstream of a throat. Fuel is mixed with the main flow to form an oil-air mixture. After ignition, the total temperature and total pressure of the main flow can be increased to realize afterburning. Moreover, since the fuel is injected into the main flow, the aerodynamic throat area of the main flow can be changed, thereby increasing the engine thrust.

The specific form of fuel import can refer to the following two methods:

1. The fuel inlet is a fuel nozzle, and the fuel nozzle is set at the sharp point of a throat, which is no more than 20% of the height of a throat from a throat. The included angle of the velocity vector direction is 0°-180°.

2. The fuel inlet is a secondary flow channel. The exit position of the secondary flow channel in the conventional throat offset type aerodynamic vectoring nozzle conforms to the position not more than 20% of the height of the first throat from the first throat.

No matter which of the above methods is applied to the conventional throat offset aerodynamic vectoring nozzle, the inner profile of the nozzle will not be changed, thereby maintaining the basic performance of the nozzle.

Further, in the present invention, the fuel is sprayed out through the fuel nozzle and mixed with the main flow, and the angle, speed and flow of the injected fuel are adjusted as required, thereby controlling the thrust vector angle of the nozzle and the aerodynamic throat area of the main flow.

Further, in the present invention, the fuel is sprayed through the secondary flow channel, and the ratio of fuel to air in the secondary flow and the size of the secondary flow are adjusted as required, thereby controlling the thrust vector angle of the nozzle and the aerodynamic throat area of the main flow.

Beneficial effect:

The invention provides a throat offset aerodynamic vectoring nozzle with the function of supplementary combustion and afterburning, which utilizes the characteristics of the internal profile of the throat offset aerodynamic vectoring nozzle and the flow field structure of the internal flow field to skillfully Fuel nozzles are arranged near the sharp point of a throat or fuel is mixed into the secondary flow injected near the throat, which fully ensures the mixing of the fuel and the main flow, and the fuel-gas mixture is ignited by the igniter, and is carried out downstream of the throat. High-efficiency combustion realizes the afterburning and afterburning function and broadens its application occasions, including the following advantages:

(1) Combining the thrust vectoring nozzle with the afterburning afterburning device, using the characteristics of its internal profile and the flow field structure of the internal flow field, the fuel nozzles arranged near a throat tip or near a throat The fuel-gas mixture is ignited by the igniter, and burned downstream of a throat to realize afterburning afterburner. There is no need to make major changes to the structure of the vectoring nozzle itself, thus ensuring vector injection. performance of the tube;

(2) It can be easily integrated with the rear fuselage of the aircraft. Regardless of whether the afterburning afterburning device is used or not, the size of the nozzle does not change, and the binary nozzle can be easily integrated with the rear fuselage of the aircraft, thereby reducing Rear body resistance, reduce the infrared radiation of the body;

(3) It is possible to control the angle, flow rate and speed of the fuel sprayed by the nozzle, or to control the flow rate, proportion and speed of the fuel in the secondary flow injected into the main flow at the primary throat, thereby controlling the thrust vector angle of the nozzle and adjusting the throat area;

(4) Make full use of the characteristics of the internal flow field of the throat offset aerodynamic vector nozzle, use its internal vortex to fully mix fuel and air, improve fuel efficiency and stabilize the flame, cancel the flame stabilizer, and reduce the structural weight ;

(5) The key technology of the nozzle can be used in conjunction with the retrofitting of other throat offset aerodynamic vectoring nozzles including reverse thrust type, vertical take-off and landing type, and omnidirectional vectoring type, and has a wide range of applications.

Description of drawings

Fig. 1 is a side view of the inner profile structure of the nozzle of the present invention.

detailed description

The present invention will be further described below in conjunction with the accompanying drawings.

The structural diagram of the internal profile of the conventional throat offset type aerodynamic vectoring nozzle shown in Figure 1 mainly consists of the upper wall surface 1 of the nozzle, the lower wall surface 2 of the nozzle, a convergence section 3 at the front of the throat, and a sharp point 4 of the throat 1. Throat 5, Second Throat Front Expansion and Convergence Section 6, Rear Body Concavity 7, Second Throat Point 8, Second Throat 9 and other components.

In the present invention, on the basis of maintaining the same internal profile of the above-mentioned conventional throat offset type aerodynamic vectoring nozzle, fuel oil is injected near a throat 5 to increase the total temperature and total pressure of the main flow, and add quality to the main flow, thereby The adjustment and control of the vector angle of the nozzle is realized, and the afterburner function is realized. Therefore, the nozzle of the present invention has two working states: normal state and afterburning afterburning state.

The normal state is used in the same way as the conventional throat offset aerodynamic vectoring nozzle, and the post-combustion afterburning state specifically includes the following two means of realization:

Realization method 1: Using the technical solution of fuel nozzles, the fuel nozzles are arranged near a throat tip 4, and the angle between the injected fuel velocity vector direction and the mainstream velocity vector direction is 0°-180°, which can be controlled by The fuel injection angle, flow rate and speed can be controlled to control the thrust vector angle, and the throat area can be adjusted by the same method.

Realization method 2: use the technical scheme of mixing fuel oil in the secondary flow, the secondary flow channel is consistent with the secondary flow channel set in the conventional throat offset aerodynamic vectoring nozzle, that is, it is located near the first throat 5, and the secondary flow channel is Whether the flow channel is mixed with fuel does not affect the arrangement form and position of the secondary flow channel, so as to maintain the performance of the thrust vector of the nozzle. Therefore, the angle at which the fuel is injected into the main flow coincides with the angle at which the fuel is injected into the secondary flow. Wherein, the secondary flow injected into the main flow at the first throat 5 can come from the engine compressor or the combustion chamber, also can come from the outlet air flow of the tail nozzle or the air intake of the aircraft or the ambient atmosphere, or can also come from gas cylinders, compressors, air pumps, etc. source.

The above is only a preferred embodiment of the present invention, it should be pointed out that for those of ordinary skill in the art, without departing from the principle of the present invention, some improvements and modifications can also be made, and these improvements and modifications are also possible. It should be regarded as the protection scope of the present invention.

Claims (6)

1. one kind has the venturi offset fluidic vectoring nozzle of afterburning boosting function, it is characterized in that: in venturi offset fluidic vectoring nozzle, be provided with fuel inlet and igniter, the position of described fuel inlet is arranged on the position that venturi longitudinal separation one venturi is not more than 20% 1 venturi height, and described igniter is arranged on a venturi downstream position.

2. the venturi offset fluidic vectoring nozzle with afterburning boosting function according to claim 1, it is characterized in that: described fuel inlet is fuel nozzle, and fuel nozzle is arranged on a venturi position of cusp place, the fuel nozzle ejection velocity vector direction of fuel oil and the angle of mainstream speed direction vector are 0 °-180 °.

3. the venturi offset fluidic vectoring nozzle with afterburning boosting function according to claim 1, is characterized in that: described fuel inlet is time circulation road.

4. one kind has the controlling method of the venturi offset fluidic vectoring nozzle of afterburning boosting function, it is characterized in that: in the scope that venturi longitudinal separation one venturi is not more than 20% 1 venturi height, inject fuel oil mix with main flow, and light in a venturi downstream position, the stagnation temperature of raising main flow and stagnation pressure change the pneumatic throat area of main flow simultaneously.

5. the controlling method with the venturi offset fluidic vectoring nozzle of afterburning boosting function according to claim 4, it is characterized in that: fuel oil is by mixing with main flow after fuel nozzle ejection, regulate the angle of ejection fuel oil, speed and flow, thus control the Thrust vector angle of jet pipe and the pneumatic throat area of main flow.

6. the controlling method with the venturi offset fluidic vectoring nozzle of afterburning boosting function according to claim 4, it is characterized in that: fuel oil is by time circulation road ejection, regulate fuel and the ratio of air and the size of secondary flow in time stream, thus the pneumatic throat area of control nozzle thrust azimuth and main flow.