Throat deviating type pneumatic thrust vectoring nozzle with fuel supplementing and thrust augmenting functions and control method

A vector nozzle and control method technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problem of having no nozzles with both aerodynamic thrust vectoring technology and afterburning afterburning technology, so as to ensure performance and reduce structural weight , The effect of improving fuel efficiency

Active Publication Date: 2016-02-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0007] 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 problems of the nozzle of afterburning afterburning technology

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  • Throat deviating type pneumatic thrust vectoring nozzle with fuel supplementing and thrust augmenting functions and control method

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Embodiment Construction

[0024] The present invention will be further described below in conjunction with the accompanying drawings.

[0025] figure 1 The structure diagram of the conventional throat offset type aerodynamic vectoring nozzle shown is mainly composed of a nozzle upper wall surface 1, a nozzle lower wall surface 2, a throat front convergent section 3, a throat sharp point 4, a The throat 5, the expansion and convergence section 6 at the front of the second throat, the rear body cavity 7, the sharp point 8 of the second throat, and the second throat 9 are composed of components.

[0026] In the present invention, on the basis of maintaining the same internal profile of the above-mentioned conventional throat offset type aerodynamic vectoring nozzle, by injecting fuel oil near a throat 5, the total temperature and total pressure of the main flow are increased, and mass is added to the main flow, thereby The adjustment and control of the vector angle of the nozzle is realized, and the afte...

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Abstract

The invention discloses a throat deviating type pneumatic thrust vectoring nozzle with fuel supplementing and thrust augmenting functions. An inner flowing channel of the nozzle comprises a front part contraction section of a first throat, the first throat, a front part expansion contraction section of a second throat, and the second throat which are arranged in sequence. The fuel supplementing and thrust augmenting functions are achieved through a fuel oil jet nozzle arranged at a top point of the first throat or achieved in a manner of doping fuel into a secondary flow filled nearby the first throat and then combusted at the downstream of the first throat. According to the method, the fuel oil injecting angle, speed and flow rate of the fuel oil jet nozzle can be controlled, or the ratio of the fuel to air in the secondary flow and the magnitude of the secondary flow rate can be controlled, so as to achieve the control of a vectoring angle of the nozzle as well as the throat area, and meanwhile, the fuel supplementing and thrust augmenting functions can be also achieved. The method is important for the accelerated flying of an aircraft adopting the throat deviating type pneumatic thrust vectoring nozzle in the air.

Description

technical field [0001] The invention relates to the field of aircraft propulsion system design, in particular to a throat offset aerodynamic vectoring nozzle. Background technique [0002] 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. [0003] At present, there are many separate designs for thrust vectoring nozzle and afterburning afterburner, but there are few designs that integrate the two ...

Claims

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Application Information

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IPC IPC(8): F02K1/78F02K1/17
Inventor 黄帅徐惊雷郭帅陈宇牛彦沣
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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