CN110284994B - Parallel thrust vector exhaust system based on throat offset type pneumatic vector spray pipe - Google Patents
Parallel thrust vector exhaust system based on throat offset type pneumatic vector spray pipe Download PDFInfo
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- CN110284994B CN110284994B CN201910387264.XA CN201910387264A CN110284994B CN 110284994 B CN110284994 B CN 110284994B CN 201910387264 A CN201910387264 A CN 201910387264A CN 110284994 B CN110284994 B CN 110284994B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
- F02K1/006—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector within one plane only
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
- F02K1/008—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector in any rearward direction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
Abstract
The invention discloses a parallel thrust vectoring exhaust system based on a throat offset type pneumatic vectoring nozzle, which comprises the throat offset type pneumatic vectoring nozzle and an adjustable Laval nozzle arranged on the outer side of the throat offset type pneumatic vectoring nozzle. The invention realizes different functions of the spray pipe by using different components, so that the spray pipe has the characteristics of high-efficiency thrust vector, adjustable wide-range flow and infrared signal reduction; by designing the smooth transition molded surface, the exhaust system has better thrust performance and vector performance in a wider working range, the evolution of the fixed geometric thrust vectoring nozzle is realized, the flight envelope of the aircraft is enlarged, and the use requirement of the aircraft is better met.
Description
Technical Field
The invention relates to a parallel thrust vectoring exhaust system based on a throat offset type pneumatic vectoring nozzle, and belongs to the technical field of advanced thrust vectoring nozzles of aircraft engines.
Background
With the development of scientific technology and the increase of practical requirements, the thrust vector aircraft engine is increasingly used by aircraft in the future. The thrust vector aircraft engine realizes the core of the thrust vector function and is a thrust vector spray pipe. The traditional mechanical thrust vectoring nozzle is complex in structure, poor in reliability and troublesome in maintenance. Therefore, it is urgent to develop a thrust vectoring nozzle with simple structure, light weight and good maintainability.
At present, the fluid thrust vectoring nozzle gradually becomes a research focus and a research hotspot of each country by the characteristics of simple structure and light weight, and will enter engineering application in the near future. Among them, the throat offset pneumatic thrust vectoring nozzle is a new type of fluid thrust vectoring nozzle which has been developed in recent years, and is more and more favored by virtue of the characteristics of simple structure, light weight, good vectoring performance and the like. The common throat offset pneumatic vectoring nozzle is of a double-throat structure, and the area of two throats is slightly larger than that of one throat, which is the most common. A small amount of gas (secondary flow) is injected into the most sensitive area (generally near one throat) in the flow field in the double-throat nozzle to generate disturbance, and the disturbance is amplified through a downstream nozzle structure, so that a stable and obvious thrust vector is realized. The throat offset pneumatic vector nozzle can be generally divided into an active type and a self-adaptive passive type, wherein the source of an air source for generating a thrust vector by the active type is mostly an external compressor, an air bottle or air introduced from a high-pressure part (mostly an air compressor) of an aeroengine, and the throat offset pneumatic vector nozzle is characterized in that the thrust vector angle changes little along with the working pressure drop ratio of the nozzle, but the thrust loss of the whole aeroengine is large; the self-adaptive passive type is characterized in that a self-adaptive bypass channel is arranged to guide high-pressure airflow at the position of an inlet (a turbine outlet) of a spray pipe to a designated position of the spray pipe for injection, self-adaptively generates disturbance and finally realizes a thrust vector.
However, most of the common throat offset type pneumatic vector nozzles are fixed-geometry nozzles, can generate a single-direction vector angle (such as a pitch direction) of about 20 degrees, and are commonly used for controlling the pitch direction of an aircraft. This means that, as the aircraft flight envelope is bigger and bigger, the requirement for adjustable nozzle flow is higher and higher, and the nozzle flow which cannot be adjusted by the nozzle with fixed geometry will have a bigger and bigger influence on the normal and efficient operation of the engine. Meanwhile, the convergence angle of the front convergence sections of the two throats inherent in the throat offset type pneumatic vectoring nozzle is too obvious, so that the convergence angle of the external profile of the rear body of the nozzle has to be very large, obvious rear body resistance can be generated under the flying condition, and the high-speed flying of an aircraft is very unfavorable. Therefore, the nozzle design scheme which not only gives consideration to the efficient and stable thrust vector function of the throat offset type pneumatic vectoring nozzle, but also can efficiently work in a wider working range of an engine to realize flow regulation, and is designed for aircraft drag reduction and integration with the rear body of an aircraft is very important, and has very high practical value.
Therefore, the parallel thrust vector exhaust system based on the throat offset type pneumatic vector spray pipe disclosed by the patent gives consideration to the requirements of a future aircraft on light weight, simple structure and thrust vector function of the spray pipe, and is convenient to integrate with the rear fuselage of the aircraft; meanwhile, the method can be combined with the practical characteristics of the work of the engine, and has the potential of further reducing the exhaust temperature of the aircraft spray pipe, so that the aircraft has stronger low infrared signals.
Disclosure of Invention
The purpose of the invention is as follows: in order to overcome the defects in the prior art, the invention provides a parallel thrust vector exhaust system based on a throat offset type pneumatic vector spray pipe, and the whole spray pipe system simultaneously has the functions of flow adjustment and thrust vector by arranging the throat offset type pneumatic vector spray pipe in the middle of the exhaust system and nesting the spray pipe scheme of a conventional Laval spray pipe outside, has the characteristics of simple structure and light weight, and has the potential of further reducing infrared radiation signals of the spray pipe.
The technical scheme is as follows: in order to achieve the purpose, the invention adopts the technical scheme that:
a parallel thrust vectoring exhaust system based on a throat offset type pneumatic vectoring nozzle comprises the throat offset type pneumatic vectoring nozzle and an adjustable Laval nozzle arranged on the outer side of the throat offset type pneumatic vectoring nozzle, wherein a thrust vector is generated by the throat offset type pneumatic vectoring nozzle through an internal and external nested parallel structure, and a flow regulation function is realized by the Laval nozzle connected to the outer side in parallel.
Furthermore, the inner profile of the inner channel throat offset type pneumatic vectoring nozzle is of a common and classical double-throat structure and specifically comprises an inner channel inlet, an inner channel equal straight section, an inner channel first throat front convergence section, an inner channel first throat, an inner channel second throat front expansion section, an inner channel second throat front convergence section and an inner channel second throat which are sequentially communicated, and the outer wall surface of the inner channel throat offset type pneumatic vectoring nozzle is used as a part of the wall surface of the laval nozzle. When the Laval nozzle is actuated, the Laval nozzle is superposed with the inner channel throat offset type pneumatic vector nozzle by adjusting the throat area and the outlet area to realize high-efficiency work in a wide range.
Two common specific implementation forms of the invention are a binary formula and a ternary axisymmetric formula. The common arrangement mode of the binary parallel thrust vectoring exhaust system is that the binary parallel thrust vectoring exhaust system is arranged up and down and is used for generating thrust vectors in the pitching direction, wherein the throat offset pneumatic vectoring nozzle is positioned in the middle inner channel, the adjustable upper wall surface and the adjustable lower wall surface and the outer wall surface of the corresponding throat offset pneumatic vectoring nozzle form an upper laval nozzle and a lower laval nozzle, namely the throat offset pneumatic vectoring nozzle in the middle is completely fixed in geometry and has no mechanical actuating device, and the upper wall surface and the lower wall surface on the outermost side can move and form the laval nozzle with the outer wall surface of the throat offset pneumatic vectoring nozzle. The basic structure of the three-element axisymmetric parallel thrust vector exhaust system is consistent with the two-element type, the two-element type configuration can be obtained by rotating along a symmetric axis, but the specific profile is slightly changed, namely, for the three-element axisymmetric type, the throat offset type pneumatic vector nozzle is used as a central inner ring channel, and an outer ring channel forms an adjustable Laval nozzle. Unless otherwise stated, the description is made in terms of binary configuration, and the ternary axisymmetric configuration can be analogized to obtain the corresponding result.
Further, the inlet of the parallel thrust vector exhaust system is connected with the outlet of an engine (a fuel gas generator). According to the connection mode, the following two types are classified, namely (1) consistency of inlet parameters of the exhaust system and (2) inconsistency of inlet parameters of the exhaust system. For practical conditions, (1) the condition that the inlet parameters of the exhaust system are consistent corresponds to the condition that the exhaust system is directly connected behind a turbofan engine or a turbojet engine after mixed exhaust. (2) The inlet parameters of the exhaust system are inconsistent, corresponding to the inner channel is connected with the inner duct of the turbofan engine, and the outer channel is connected with the outer duct of the turbofan engine, in this case, the air flow temperature of the outer channel (Laval nozzle channel) is obviously lower than that of the inner channel (throat offset pneumatic vector nozzle channel), so the exhaust temperature and the infrared radiation signals of the whole exhaust system can be obviously reduced.
Further, when designing the parallel exhaust system, the flow matching of the nozzle and the engine needs to be carefully matched, and particularly the adjustment relation between the throat and the outlet area of the laval nozzle channel is obtained.
Aiming at the condition that the inlet parameters of the inner channel and the outer channel of the exhaust system are consistent, the pressure drop ratio of the inner channel and the outer channel of the whole exhaust system is consistent, therefore, the flow of the throat offset type pneumatic vector nozzle of the inner channel is determined by a throat area and the total pressure of incoming flow to obtain a fixed value, the flow which needs to flow through the laval channel can be obtained, the area of the throat of the outer laval nozzle at the moment can be obtained in a reverse manner only by combining the inlet total pressure of the outer laval nozzle at the moment, and then the change rule of the throat area of the outer laval nozzle channel, which changes along with the pressure drop ratio, is obtained.
And aiming at the condition that the inlet parameters of the inner channel and the outer channel of the exhaust system are inconsistent, the flow regulation of the outer Laval nozzle only needs to be matched with the flow and the total pressure of the outer duct of the engine. Furthermore, if the working ranges of the inner channel and the outer channel of the engine are greatly changed, a pressure difference pneumatic valve capable of adjusting the flow of the inner channel and the outer channel needs to be arranged at the equal straight section of the throat offset type pneumatic vectoring nozzle, and the flow adjustment of the two channels is realized by automatically opening the valve under the action of the pressure difference. In most cases, after the differential pressure pneumatic valve is actuated, the air flow of the inner channel leaks to the outer laval nozzle, the stable work of the inner channel and the realization of a mechanism for adjusting the outer channel should be preferentially met, at this moment, the flow of the outer channel is the sum of the flow of the outer duct of the engine and the flow added by air leakage, the average total pressure of the outer channel is the average total pressure of the mass of the two air flows, and the throat area change adjusting rule of the outer laval nozzle can be obtained based on the above relation.
Further, from the design point of view of the exhaust system, after the specific connection mode of the exhaust system and the turbine rear section of the engine is determined, the inlet area ratio of the inner side nozzle and the outer side nozzle can be determined through the relevant size of the turbine rear section of the engine. Taking the consistency of the thrust vector inlet parameters as an example, after the engine exhaust system is known to be in the full envelope range, the relevant parameters such as total pressure, flow and total temperature in the full envelope working range can be determined. At the moment, the flow variation range of the inner channel throat offset type pneumatic vectoring nozzle is determined according to the variation range of the total pressure, then the flow of the outer side Laval nozzle can be obtained after the flow variation range is compared with the exhaust system, and the inlet area of the outer side Laval nozzle can be further determined by aiming at the outer side Laval nozzle through a flow continuity equation and a Bernoulli equation.
Further, the outboard laval nozzle may be divided into an equal straight section (before section a), an offset flow section (section a to section B), a converging section (section B to section C), a throat section (section C), and a diverging section (after section C). The bias rectifying section is an S-shaped bent pipe, the outer channel airflow is biased towards the center through the S-shaped bent pipe, and conditions are created for the downstream to use the outer wall surface corresponding to the turning position of the expansion and convergence section of the two throats of the throat offset pneumatic vectoring nozzle as a throat; meanwhile, the offset rectifying section is an expansion flow channel, namely the area of an outlet is larger than that of an inlet, so that the purposes of speed reduction, rectification and static pressure improvement are achieved. The convergent section is connected with the offset rectifying section and the divergent section, and particularly, the tangent line of the outer wall surface of the throat offset pneumatic vectoring nozzle is required to be horizontal when the convergent section is close to an outlet so as to realize the coanda flow of the divergent section in a vectoring state, reduce the vector angle reduction degree and increase the vector angle under the condition of certain pressure drop ratio NPR. The section C is the throat section of the Laval nozzle, and one side of the section C is an outer wall surface corresponding to the turning part of the expansion and convergence section of the two throats of the throat offset pneumatic vectoring nozzle. The expansion section is positioned at the downstream of the cross section of the throat and consists of a Laval nozzle and the outer wall surface of the convergence section of the expansion and convergence section of the two throats of the throat offset pneumatic vector nozzle, wherein the tangent line of the outer wall surface of the convergence section of the expansion and convergence section of the two throats of the throat offset pneumatic vector nozzle at the throat is required to be horizontal, the subsequent molded line is a continuous and monotonous curve, and the typical configuration is a secondary curve (such as a part of a circle, an ellipse and a parabola) so as to reduce the vector angle reduction degree of the exhaust system under the working condition of high pressure drop ratio through the wall attachment effect and ensure better vector performance, and meanwhile, the outlet of the expansion section (namely the outlet of the Laval nozzle) is required to be positioned at the downstream of the outlet of the throat offset pneumatic vector nozzle, otherwise, the effect of improving the flow field outside the nozzle cannot be realized. And the tail part of the movable part of the expansion section also needs to be a smooth continuous curve as much as possible so as to meet the requirement of airflow wall attachment flow.
Furthermore, the outlet section of the outer Laval nozzle forms a certain angle with the horizontal direction (the normal direction of the outlet section of the throat offset pneumatic vectoring nozzle). The included angle between the plane and the horizontal direction cannot be larger than 115% -130% of the maximum vector angle of the designed working point of the inner channel throat offset type pneumatic vector nozzle, and cannot be smaller than 45% -60% of the maximum vector angle of the designed working point of the inner channel throat offset type pneumatic vector nozzle. Through the design, the exhaust direction of the Laval nozzle can be effectively controlled to be fully driven by the vector deflection of the throat offset type pneumatic vector nozzle, and a larger vector angle is realized.
The example is explained with a binary pitch placement and vector deflection down. Under a certain pressure drop ratio, the airflow of the throat offset type pneumatic vector nozzle deflects downwards, and the airflow of the lower Laval nozzle channel can be extruded, so that the airflow of the deflected jet of the throat offset type pneumatic vector nozzle and the gap between the wall surface of the lower Laval nozzle flow. If the included angle between the outlet plane of the laval nozzle and the horizontal direction is too small, the expansion of jet flow flowing out of the laval nozzle at the lower side is very easy to be limited, the jet flow cannot be fully expanded to generate high-efficiency thrust, and the tail part of the expansion section of the laval nozzle cannot be bent to flow along the wall to generate a large vector angle, so that the jet flow deflection after the throat deflection type pneumatic vector nozzle is further prevented, and the vector angle is further reduced. However, if the included angle between the exit plane of the laval nozzle and the horizontal direction is too large, the airflow of the upper laval nozzle channel cannot be deflected by the smooth continuous curved surface of the trailing edge of the upper outer wall surface (outer wall surface of the convergent section) of the throat offset type pneumatic vectoring nozzle under the disturbance of the low-pressure area generated by the jet deflection of the throat offset type pneumatic vectoring nozzle, so that the total vectoring angle is reduced.
Further, the actuation mode of the outer laval nozzle can be, but is not limited to, the following: (1) a double hinge scheme of rotating around a front hinge, (2) a double hinge scheme of rotating around a rear hinge, (3) a single hinge scheme around a front hinge, (4) a sliding scheme of taking a front profile as a rail, and (5) a sliding scheme of taking a rear profile as a rail. Wherein, the schemes are all suitable for binary configuration, namely, a flat plate structure is arranged between the hinges. When the three-axis symmetric configuration is required to be adapted, the flat plate structure needs to be changed into a fish scale structure. Meanwhile, the throat area of the laval nozzle can be changed simultaneously by (1) a double-hinge scheme rotating around a front hinge, (2) a double-hinge scheme rotating around a rear hinge, (4) a sliding scheme taking a front profile as a track, and (5) a sliding scheme taking a rear profile as a track; (1) the double hinge solution rotating around the front hinge, (4) the sliding solution with front profile as track and (5) the sliding solution with rear profile as track can change the exit area of the laval nozzle. (3) Whether the throat area can be changed by the single hinge scheme around the front hinge depends on the position of the hinge, generally speaking, the hinge is arranged at the upstream of the turning part of the front expanding and converging section of the two throats of the throat offset type pneumatic vector nozzle so as to meet the condition that the outer channel is the Laval nozzle.
Has the advantages that: compared with the prior art, the parallel thrust vector exhaust system based on the throat offset type pneumatic vector nozzle provided by the invention has the following advantages:
(1) compared with the traditional throat offset pneumatic vectoring nozzle, the invention meets the flow cross section shape of the nozzle under the wide-range working condition by changing the nozzle structure and adopting a parallel structure, thereby enlarging the flight envelope;
(2) by the parallel structure, the outer wall surface of the throat offset type pneumatic vector nozzle is prevented from being directly contacted with the outflow of high-speed flight, and the flight resistance of the rear body is reduced;
(3) the development direction of the aerodynamic-stealth integrated design of the rear fuselage of the aircraft is met, the exhaust temperature of the aircraft can be obviously reduced, the infrared signal of a spray pipe is reduced, and the infrared stealth performance is improved;
(4) the thrust vector and the flow regulation are realized in a parallel connection mode, the inner channel generates a stable and obvious thrust vector, the outer channel performs flow regulation, the flow field of the jet pipe afterbody is improved, and the afterbody resistance is reduced;
(5) the same idea can be used in other types of fixed combination pneumatic thrust vectoring nozzle, and the device has universality and wide application.
Drawings
FIG. 1 is a parallel flow cross-sectional view of the present invention employing a dual hinge arrangement for rotation about a front hinge;
FIG. 2 is a parallel flow cross-sectional view of the present invention employing a dual hinge arrangement for rotation about the rear hinge;
FIG. 3 is a parallel flow cross-sectional view of the present invention using a single hinge approach around the front hinge;
FIG. 4 is a cross-sectional view in parallel flow of the present invention using a sliding version with the front profile being the rail;
FIG. 5 is a cross-sectional view in parallel flow of the present invention using a sliding version with the back profile as the rail;
FIG. 6 is a numerically calculated Mach number cloud when NPR is 4 for an embodiment of the present invention;
fig. 7 is a graph of numerical calculations for an embodiment of the present invention when NPR is 4;
the figure includes: 1. the nozzle comprises a Laval nozzle, a throat offset type pneumatic vectoring nozzle 2, an inner runner inlet 3, an outer runner inlet 4, an outer runner inlet 5, a differential pressure pneumatic valve 6, an inner runner equal straight section 7, an inner runner one-throat front convergence section 8, an inner runner one-throat 9, an inner runner two-throat front expansion convergence section 10, an outer runner throat section 11, an inner runner two-throat 12 and an outlet section of the Laval nozzle.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and examples.
As shown in fig. 1-2, the parallel thrust vectoring exhaust system based on the throat offset type pneumatic vectoring nozzle comprises a throat offset type pneumatic vectoring nozzle 2 and an adjustable laval nozzle 1 arranged outside the throat offset type pneumatic vectoring nozzle 2, wherein thrust vectoring is generated by the throat offset type pneumatic vectoring nozzle 2 through an internal and external nested parallel structure, and a flow regulation function is realized by the laval nozzle 1 connected outside in parallel.
The inner profile of the inner channel throat offset type pneumatic vectoring nozzle is of a common and classical double-throat structure and specifically comprises an inner channel inlet 3, an inner channel equal straight section 6, an inner channel first throat front convergence section 7, an inner channel first throat 8, an inner channel second throat front expansion convergence section 11 and an inner channel second throat 11 which are sequentially communicated, and the outer wall surface of the inner channel throat offset type pneumatic vectoring nozzle forms the inner wall surface of the Laval nozzle 1. When the Laval nozzle is actuated, the Laval nozzle is superposed with the inner channel throat offset type pneumatic vector nozzle by adjusting the throat area and the outlet area to realize high-efficiency work in a wide range.
Two common specific implementation forms of the invention are a binary formula and a ternary axisymmetric formula. The common arrangement mode of the binary parallel thrust vectoring exhaust system is that the binary parallel thrust vectoring exhaust system is arranged up and down and is used for generating thrust vectors in the pitching direction, wherein the throat offset pneumatic vectoring nozzle is positioned in the middle inner channel, the adjustable upper wall surface and the adjustable lower wall surface and the outer wall surface of the corresponding throat offset pneumatic vectoring nozzle form an upper laval nozzle and a lower laval nozzle, namely the throat offset pneumatic vectoring nozzle in the middle is completely fixed in geometry and has no mechanical actuating device, and the upper wall surface and the lower wall surface on the outermost side can move and form the laval nozzle with the outer wall surface of the throat offset pneumatic vectoring nozzle. The basic structure of the three-element axisymmetric parallel thrust vector exhaust system is consistent with the two-element type, the two-element type configuration can be obtained by rotating along a symmetric axis, but the specific profile is slightly changed, namely, for the three-element axisymmetric type, the throat offset type pneumatic vector nozzle is used as a central inner ring channel, and an outer ring channel forms an adjustable Laval nozzle. Unless otherwise stated, the description is made in terms of binary configuration, and the ternary axisymmetric configuration can be analogized to obtain the corresponding result.
Further, the inlet of the parallel thrust vector exhaust system is connected with the outlet of an engine (a fuel gas generator). According to the connection mode, the following two types are classified, namely (1) consistency of inlet parameters of the exhaust system and (2) inconsistency of inlet parameters of the exhaust system. For practical conditions, (1) the condition that the inlet parameters of the exhaust system are consistent corresponds to the condition that the exhaust system is directly connected behind a turbofan engine or a turbojet engine after mixed exhaust. (2) The inlet parameters of the exhaust system are inconsistent, corresponding to the inner channel is connected with the inner duct of the turbofan engine, and the outer channel is connected with the outer duct of the turbofan engine, in this case, the air flow temperature of the outer channel (Laval nozzle channel) is obviously lower than that of the inner channel (throat offset pneumatic vector nozzle channel), so the exhaust temperature and the infrared radiation signals of the whole exhaust system can be obviously reduced.
Further, when designing the parallel exhaust system, the flow matching of the nozzle and the engine needs to be carefully matched, and particularly the adjustment relation between the throat and the outlet area of the laval nozzle channel is obtained.
Aiming at the condition that the inlet parameters of the inner channel and the outer channel of the exhaust system are consistent, the pressure drop ratio of the inner channel and the outer channel of the whole exhaust system is consistent, therefore, the flow of the throat offset type pneumatic vector nozzle of the inner channel is determined by a throat area and the total pressure of incoming flow to obtain a fixed value, the flow which needs to flow through the laval channel can be obtained, the area of the throat of the outer laval nozzle at the moment can be obtained in a reverse manner only by combining the inlet total pressure of the outer laval nozzle at the moment, and then the change rule of the throat area of the outer laval nozzle channel, which changes along with the pressure drop ratio, is obtained.
And aiming at the condition that the inlet parameters of the inner channel and the outer channel of the exhaust system are inconsistent, the flow regulation of the outer Laval nozzle only needs to be matched with the flow and the total pressure of the outer duct of the engine. Further, if the working ranges of the inner channel and the outer channel of the engine are changed greatly, a pressure difference pneumatic valve 5 capable of adjusting the flow of the inner channel and the outer channel needs to be arranged at the equal straight section of the throat offset type pneumatic vectoring nozzle, and the flow adjustment of the two channels is realized by automatically opening the valve under the action of the pressure difference. In most cases, after the differential pressure pneumatic valve 5 is actuated, the air flow of the inner channel leaks to the outer laval nozzle, the stable operation of the inner channel and the realization of a mechanism for adjusting the outer channel should be preferentially met, at this time, the flow of the outer channel is the sum of the flow of the outer duct of the engine and the flow added by air leakage, the average total pressure of the outer duct is the average total pressure of the mass of the two air flows, and the throat area change adjusting rule of the outer laval nozzle can be obtained based on the above relation.
Further, from the design point of view of the exhaust system, after the specific connection mode of the exhaust system and the turbine rear section of the engine is determined, the inlet area ratio of the inner side nozzle and the outer side nozzle can be determined through the relevant size of the turbine rear section of the engine. Taking the consistency of the thrust vector inlet parameters as an example, after the engine exhaust system is known to be in the full envelope range, the relevant parameters such as total pressure, flow and total temperature in the full envelope working range can be determined. At the moment, the flow variation range of the inner channel throat offset type pneumatic vectoring nozzle is determined according to the variation range of the total pressure, then the flow of the outer side Laval nozzle can be obtained after the flow variation range is compared with the exhaust system, and the inlet area of the outer side Laval nozzle can be further determined by aiming at the outer side Laval nozzle through a flow continuity equation and a Bernoulli equation.
Further, the outboard laval nozzle may be divided into an equal straight section (before section a), an offset flow section (section a to section B), a converging section (section B to section C), a throat section (section C), and a diverging section (after section C). The bias rectifying section is an S-shaped bent pipe, the outer channel airflow is biased towards the center through the S-shaped bent pipe, and conditions are created for the downstream to use the outer wall surface corresponding to the turning position of the expansion and convergence section of the two throats of the throat offset pneumatic vectoring nozzle as a throat; meanwhile, the offset rectifying section is an expansion flow channel, namely the area of an outlet is larger than that of an inlet, so that the purposes of speed reduction, rectification and static pressure improvement are achieved. The convergent section is connected with the offset rectifying section and the divergent section, and particularly, the tangent line of the outer wall surface of the throat offset pneumatic vectoring nozzle is required to be horizontal when the convergent section is close to an outlet so as to realize the coanda flow of the divergent section in a vectoring state and reduce the vector angle reduction degree. The section C is the throat section of the Laval nozzle, and one side of the section C is an outer wall surface corresponding to the turning part of the expansion and convergence section of the two throats of the throat offset pneumatic vectoring nozzle. The expansion section is positioned at the downstream of the cross section of the throat and consists of a Laval nozzle and the outer wall surface of the convergence section of the expansion and convergence section of the two throats of the throat offset pneumatic vector nozzle, wherein the tangent line of the outer wall surface of the convergence section of the expansion and convergence section of the two throats of the throat offset pneumatic vector nozzle at the throat is required to be horizontal, the subsequent molded line is a continuous and monotonous curve, and the typical configuration is a secondary curve (such as a part of a circle, an ellipse and a parabola) so as to reduce the vector angle reduction degree of the exhaust system under the working condition of high pressure drop ratio through the wall attachment effect and ensure better vector performance, and meanwhile, the outlet of the expansion section (namely the outlet of the Laval nozzle) is required to be positioned at the downstream of the outlet of the throat offset pneumatic vector nozzle, otherwise, the effect of improving the flow field outside the nozzle cannot be realized. And the tail part of the movable part of the expansion section also needs to be a smooth continuous curve as much as possible so as to meet the requirement of airflow wall attachment flow.
Further, the outlet section 12 of the outer laval nozzle is angled from horizontal (normal to the outlet section of the throat offset aerodynamic vectoring nozzle). The included angle between the plane and the horizontal direction cannot be larger than 115% -130% of the maximum vector angle of the designed working point of the inner channel throat offset type pneumatic vector nozzle, and cannot be smaller than 45% -60% of the maximum vector angle of the designed working point of the inner channel throat offset type pneumatic vector nozzle. Through the design, the exhaust direction of the Laval nozzle can be effectively controlled to be fully driven by the vector deflection of the throat offset type pneumatic vector nozzle, and a larger vector angle is realized.
The example is explained with a binary pitch placement and vector deflection down. Under a certain pressure drop ratio, the airflow of the throat offset type pneumatic vector nozzle deflects downwards, and the airflow of the lower Laval nozzle channel can be extruded, so that the airflow of the deflected jet of the throat offset type pneumatic vector nozzle and the gap between the wall surface of the lower Laval nozzle flow. If the included angle between the outlet plane of the laval nozzle and the horizontal direction is too small, the expansion of jet flow flowing out of the laval nozzle at the lower side is very easy to be limited, the jet flow cannot be fully expanded to generate high-efficiency thrust, and the tail part of the expansion section of the laval nozzle cannot be bent to flow along the wall to generate a large vector angle, so that the jet flow deflection after the throat deflection type pneumatic vector nozzle is further prevented, and the vector angle is further reduced. However, if the included angle between the exit plane of the laval nozzle and the horizontal direction is too large, the airflow of the upper laval nozzle channel cannot be deflected by the smooth continuous curved surface of the trailing edge of the upper outer wall surface (outer wall surface of the convergent section) of the throat offset type pneumatic vectoring nozzle under the disturbance of the low-pressure area generated by the jet deflection of the throat offset type pneumatic vectoring nozzle, so that the total vectoring angle is reduced.
Further, the actuation mode of the outer laval nozzle can be, but is not limited to, the following: (1) a double hinge solution rotating around the front hinge, (2) a double hinge solution rotating around the rear hinge, (3) a single hinge solution around the front hinge, (4) a sliding solution with the front profile as a rail, (5) a sliding solution with the rear profile as a rail, as shown in fig. 3-5.
Specifically, (1) the double-hinge scheme of rotating around the front hinge, its acting wall includes outer wall of convergent section of outer flow path and outer wall of divergent section of outer flow path, two hinges are set up in the front end of outer wall of convergent section of outer flow path and outer wall of divergent section of outer flow path separately, the position of the second hinge is that the throat section of outer flow path 10 locates, at this moment, the Laval spray tube can be under the drive of actuating mechanism, the entrance area of Laval spray tube keeps unchanged, change Laval spray tube throat area and total area of outlet; (2) the double-hinge scheme of rotating around the rear hinge is characterized in that the acting wall surface of the double-hinge scheme is also an outer wall surface of an outer flow channel convergence section and an outer wall surface of an outer flow channel expansion section, the two hinges are respectively arranged at the tail ends of the outer wall surface of the outer flow channel convergence section and the outer wall surface of the outer flow channel expansion section, the position of the first hinge is the position of the section 10 of the throat of the outer flow channel, at the moment, the Laval nozzle can be driven by the actuating mechanism, the outlet area of the Laval nozzle is kept unchanged, and the throat area and the total inlet area of the Laval nozzle are changed; (3) the single hinge scheme around the front hinge has the advantages that the movable wall surface only has the outer wall surface of the outer flow channel expansion section, only one hinge is positioned at the section 10 of the throat of the outer flow channel, the non-adjustable convergence section of the hinge is contained in the fixed part, and at the moment, the inlet area of the Laval nozzle and the throat area of the Laval nozzle are kept unchanged under the driving of the actuating mechanism, so that the total inlet area is changed; (4) the sliding type scheme that the front profile is a track and the sliding type scheme that the rear profile is a track (5) are both variants of the actuating mechanism, and the change of the flow section area of the laval nozzle is realized by changing the rotating structure into the translational profile, so that the adjustment of the nozzle is realized.
Wherein, the schemes are all suitable for binary configuration, namely, a flat plate structure is arranged between the hinges. When the three-axis symmetric configuration is required to be adapted, the flat plate structure needs to be changed into a fish scale structure. Meanwhile, the throat area of the laval nozzle can be changed simultaneously by (1) a double-hinge scheme rotating around a front hinge, (2) a double-hinge scheme rotating around a rear hinge, (4) a sliding scheme taking a front profile as a track, and (5) a sliding scheme taking a rear profile as a track; (1) the double hinge solution rotating around the front hinge, (4) the sliding solution with front profile as track and (5) the sliding solution with rear profile as track can change the exit area of the laval nozzle. (3) Whether the throat area can be changed by the single hinge scheme around the front hinge depends on the position of the hinge, generally speaking, the hinge is arranged at the upstream of the turning part of the front expanding and converging section of the two throats of the throat offset type pneumatic vector nozzle so as to meet the condition that the outer channel is the Laval nozzle.
Furthermore, the invention can realize the aims of reducing infrared signals and improving the rear body flow field in a similar way through certain simplification. Namely, the adjusting mechanism (such as a hinge, an actuating mechanism and the like) of the outer Laval nozzle is eliminated, and the outer Laval nozzle is changed into a cylinder with fixed geometry. In this case, the throat offset aerodynamic vectoring nozzle is spaced from the outer cylinder by a small distance, preferably 85% or more, and the outer cylinder profile outlet may be convergent or slightly convergent-divergent (i.e., laval nozzle), but preferably is convergent nozzle. Meanwhile, in consideration of the aspect of integration with the rear body, the convergence angle of the convergence section is not more than 10 degrees, and 15 degrees is taken as a limit.
Further, under the current typical exhaust system configuration, the total vector angle of the exhaust system is smaller than that of a single throat offset type pneumatic vector nozzle under the same pressure drop ratio in most cases, but the specific small degree is greatly influenced by the flow ratio of the inner channel and the outer channel, the molded line of the outer wall surface of the throat offset type pneumatic vector nozzle and the molded line of the laval nozzle. And setting the vector angle reference value of the exhaust system as the average of the vector angle and the mass flow of each channel, wherein the vector angle of the channel of the Laval nozzle is 0. On the basis, the final vector angle can be 200-400% of the reference value under the ideal condition by optimizing the molded line, but if the molded line is unsmooth in design and poor in adherent flow effect, the final vector angle can be 60-75% of the reference value at the minimum. Therefore, the design of the molded line is very important, and the core of the molded line is (1) the outer wall surface of the expansion and convergence section of the throat offset pneumatic vectoring nozzle, particularly the smooth and continuous part near the turning part, the tangent line at the channel of the Laval nozzle is horizontal, and (2) the tail part of the Laval nozzle is smoothly turned, so that the airflow is easy to attach to the wall.
Further, under the condition that the weight gain of the mechanical structure is controllable, the outer Laval nozzle channel can be upgraded from the function of simply adjusting the area and the flow of the nozzle throat to the nozzle with the mechanical hydraulic thrust vector function, at the moment, the inner channel and the outer channel both have the thrust vector function, and the vector angle is larger. However, the structure is more complex and is generally not recommended.
Further, in the case of a binary configuration, the inner and outer channels are fixedly connected by the side wall surfaces. The inner and outer channels of the three-dimensional axisymmetric configuration are connected through a fixed support plate connecting the inner and outer channels.
The principle, the gas injection position, the gas injection angle and the like of the inner channel throat offset type pneumatic vectoring nozzle for realizing the gas flow direction control are consistent with those of the conventional throat offset type pneumatic vectoring nozzle, and the details are not repeated. Meanwhile, the application range of the invention can simultaneously meet the requirements of the throat offset type pneumatic vectoring nozzle of an active type and a self-adaptive passive type.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Examples
The method is used for calculating a parallel thrust vector exhaust system based on the throat offset type pneumatic vector nozzle in a typical configuration.
Fig. 6 shows a numerical computation mach number cloud when its NPR is 4. It can be seen that through the preliminary molded line optimization design, when the vector deflects downwards, the airflow of the Laval channel of the upper side channel is not ejected backwards, but flows along the outer wall surface of the throat offset type pneumatic vector nozzle to be attached to the wall under the disturbance of the central throat offset type pneumatic vector nozzle, so that the deflection is realized. Meanwhile, the airflow of the lower side channel flows along the tail curved surface of the nozzle Laval channel and deflects downwards together, so that better vector performance is realized.
Fig. 7 shows the data calculation curve thereof. The BDTN basic is a curve of a vector angle of the throat offset type pneumatic vector nozzle with the same profile along with the change of the drop pressure ratio NPR, BDTN-ejector1 is calculated data of the profile of the upper graph, BDTN-ejector2 is calculated data of the profile which is similar to the profile of the upper graph but is in the aspects of the outer wall surface of the throat offset type pneumatic vector nozzle and the tail curve of the Laval nozzle. It can be seen that the relevant critical profile has a significant impact on nozzle performance.
Claims (3)
1. A parallel thrust vectoring exhaust system based on a throat offset type pneumatic vectoring nozzle is characterized by comprising a throat offset type pneumatic vectoring nozzle (2) and an adjustable Laval nozzle (1) arranged on the outer side of the throat offset type pneumatic vectoring nozzle (2), wherein a thrust vector is generated by the throat offset type pneumatic vectoring nozzle (2) through an internally-externally nested parallel structure, and a flow regulation function is realized by the Laval nozzle (1) which is connected in parallel on the outer side;
the inner runner of the throat offset type pneumatic vectoring nozzle (2) comprises an inner runner inlet (3), an inner runner equal straight section (6), an inner runner one-throat front convergence section (7), an inner runner one-throat (8), an inner runner two-throat front expansion convergence section (9) and an inner runner two-throat (11) which are sequentially communicated, and the outer wall surface of the inner runner comprises the inner wall surface of the Laval nozzle (1);
the flow channel of the Laval nozzle (1) comprises an outer flow channel inlet (4), an outer flow channel equal straight section, an outer flow channel offset rectifying section, an outer flow channel converging section, an outer flow channel throat section (10) and an outer flow channel expanding section which are sequentially communicated;
the outer runner offset rectifying section is an expansion runner formed by a section of S bent pipe and is used for realizing center offset and deceleration rectification of the airflow of the outer channel; the throat offset pneumatic vectoring nozzle (2) at the section (10) of the outer runner throat has a horizontal outer wall tangent, and the outlet of the outer runner expansion section is positioned at the downstream of the outlet of the throat offset pneumatic vectoring nozzle (2);
the included angle between the outlet section (12) of the Laval nozzle and the horizontal direction is not more than 130% of the maximum vector angle of the designed working point of the throat offset type pneumatic vectoring nozzle (2) and not less than 45% of the maximum vector angle of the designed working point of the throat offset type pneumatic vectoring nozzle (2).
2. A parallel thrust vectoring exhaust system based on throat offset aerodynamic vectoring nozzle according to claim 1, characterized in that the implementation form of the parallel thrust vectoring exhaust system comprises a binary type and a ternary axial symmetry type, wherein two Laval nozzles (1) of the binary type parallel thrust vectoring exhaust system are arranged up and down symmetrically for generating thrust vectoring in the pitching direction, and the ternary axial symmetry type parallel thrust vectoring exhaust system uses the throat offset aerodynamic vectoring nozzle (2) as a central inner ring channel, and the outer ring channel forms the adjustable Laval nozzle (1).
3. A parallel thrust vectoring exhaust system according to claim 1 wherein the profile of the outer flow path diverging section is a smooth continuous curve.
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| CN111577675A (en) * | 2020-05-25 | 2020-08-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ejector with adjustable throat |
| CN111622861A (en) * | 2020-06-19 | 2020-09-04 | 中国人民解放军总参谋部第六十研究所 | Engine tail nozzle adjusting method and device |
| CN112177794B (en) * | 2020-08-21 | 2022-01-04 | 南京航空航天大学 | Throat offset type pneumatic vectoring nozzle and design method thereof |
| CN112855380B (en) * | 2020-12-02 | 2022-05-03 | 南京航空航天大学 | Flow regulating device of axisymmetric channel, tail nozzle using same and regulating method |
| CN113027633B (en) * | 2021-03-01 | 2022-01-18 | 南京航空航天大学 | Combined vectoring nozzle system and control method thereof |
| CN113190913B (en) * | 2021-03-30 | 2024-03-29 | 南京航空航天大学 | Matching design method for axisymmetric cross-medium water-air amphibious aircraft power system |
| CN114087087B (en) * | 2021-10-29 | 2023-03-31 | 南京航空航天大学 | Multi-principle multi-mode pneumatic thrust vectoring nozzle and control method |
| CN114810414B (en) * | 2022-04-19 | 2023-09-19 | 清华大学 | Vector adjustment spray pipe and self-adaptive variable cycle engine |
| CN115077921B (en) * | 2022-07-21 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Binary vector nozzle engine outfield test calibration and ground simulation system |
| CN115653779A (en) * | 2022-10-13 | 2023-01-31 | 中国航发四川燃气涡轮研究院 | Multi-shaft pneumatic thrust vectoring nozzle and multi-shaft thrust adjusting method |
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