CN202628279U - Binary hypersonic speed-variable geometric air inlet channel - Google Patents
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- CN202628279U CN202628279U CN 201220233265 CN201220233265U CN202628279U CN 202628279 U CN202628279 U CN 202628279U CN 201220233265 CN201220233265 CN 201220233265 CN 201220233265 U CN201220233265 U CN 201220233265U CN 202628279 U CN202628279 U CN 202628279U
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- 238000002955 isolation Methods 0.000 abstract 1
- 230000035939 shock Effects 0.000 description 19
- 238000000034 method Methods 0.000 description 11
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- 238000007906 compression Methods 0.000 description 10
- 238000002485 combustion reaction Methods 0.000 description 9
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- 238000004088 simulation Methods 0.000 description 3
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Abstract
The utility model relates to a binary hypersonic speed-variable geometric air inlet channel, and belongs to the field of aerodynamic designs of air inlet channels. The air inlet channel consists of a compressed surface, a contraction section in the air inlet channel, a unidiameter isolation section and a lip cover, and is characterized in that the lip cover has a structure which can translate forward and backward along a flow incoming direction. By easily translating the lip cover forward and backward along the flow incoming direction, the adjustment of the air inlet channel from a closed state to an open state, the adjustment of the internal contraction ratio in a high mach number state and a low mach number state, and the adjustment of the flow capture under different incoming flow conditions in a normal working range are realized.
Description
Technical field
The utility model is related to a kind of hypersonic change geometry air intake duct of binary, belongs to air intake duct pneumatic design field.
Background technology
For airbreather, excellent aeroperformance of the air intake duct under design point is it cannot be guaranteed that it can work normal table under all crucial working conditions.The hypersonic airbreather worked especially for wide range of Mach numbers, when in non-design work state, it will be the major criterion of evaluating air intake duct synthetic aerodynamic performance that can air intake duct provide air mass flow that is enough, meeting certain flow quality requirement by engine of less resistance and flow losses.
Subsonic inlet and engine flow matches applied to low-speed operations device is relatively easy, when state of flight changes, air intake duct can automatically adjust the relation between free stream tube area and capture area to realize automatically adjusting for flow according to engine to the demand of flow.As aircraft flight envelope curve gradually expands, flying speed gradually expands to supersonic speed by subsonic speed, hypersonic, and it is difficult the job requirement for meeting wide range of Mach numbers to determine geometry air intake duct.Now, air intake duct becomes geometry designs technology air intake duct and engine flow matches in the case where solving off design point, and advantage is shown in terms of low mach self-starting, is gradually recognized and is paid attention to extensively by industry.Circulated in addition, being combined for turbine base（The turbine-based combined cycle, TBCC）And rocket based combined cycle（The rocket-based combined cycle, RBCC）And Dual-mode Scramjet（Dual-Mode Scramjet）For, become geometry air intake duct be solve it is each promote between circulation co-ordination and realize the optimal selection of mode conversion, will take off the important guarantee worked up to the wide Mach number scope propulsion system normal table of supersonic and hypersonic with time-varying geometry air intake duct as aircraft from ground.
In view of becoming the aeroperformance advantage that geometry air intake duct works in wide range of Mach numbers, especially in hypersonic field, scholars have carried out substantial amounts of research work.The mechanisms such as French ONERA propose a kind of change geometry Dual-mode Scramjet concept for translating lip.By mobile outer lip cover in the horizontal direction, make air intake duct that there is larger contract in High Mach number than with the compression effective to high velocity air progress；There is less contract Billy in intake duct starting during low mach.Japanology mechanism ISAS devises supersonic speed mixed pressure formula axial symmetry for the ATREX of its research and becomes geometry air intake duct, by the regulation that air intake duct wave system is realized along axis translation center cone.
It is can be found that from the analysis grasped, the problem of substantial amounts of change geometry air intake duct scheme only concentrates solution single aspect, solve the poor contradiction small with decrement in High Mach number of low mach flow capture in such as capture of low mach flow or low mach starting problem, scheme simultaneously well and consider regulation of the air intake duct from the wider range of Mach numbers aeroperformance for being opened into normal work of relay point Mach number.
Utility model content
The utility model is wide for hypersonic propulsion system working range, acutely causes air intake duct aeroperformance to deteriorate to flow Parameters variation, it is proposed that a kind of binary is hypersonic to become geometry air intake duct and method for designing and working method.Realize the regulation from closed mode to opening by simply along direction of flow anterior-posterior translation lip cover, making air intake duct, High Mach number state and low mach state contract than regulation, the regulation of different inlet flow conditions down-offs captures in normal range of operation.
A kind of binary is hypersonic to become geometry air intake duct, by compressing surface, air intake duct contract section, isolator and lip cover composition；It is characterized in that：Above-mentioned lip cover is can be along direction of flow anterior-posterior translation formula structure；And the geometric parameter of air intake duct meets below equation
（1）
Wherein K is the ratio between High Mach number contract ratio and low mach contract ratio in air intake duct normal range of operation；For air intake duct High Mach number contract ratio, the i.e. upper limit of normal range of operation,
For air intake duct low mach contract ratio, the i.e. lower limit of normal range of operation,
WithIt is given by specific aerial mission；
The distance of low mach state translation is moved to from High Mach number state for air intake duct lip cover,
For High Mach number state air intake duct contract section outlet height,For High Mach number state air intake duct contract section entrance height；
For air intake duct contract section porch compressing surface and the angle of horizontal direction,
For air intake duct isolator and the angle of horizontal direction.
The hypersonic method for designing for becoming geometry air intake duct of the binary, it is characterised in that High Mach number is determined according to aerial mission first（The upper limit of flight range）Air intake duct contract ratioAnd low mach（The lower limit of flight range）Air intake duct contract ratio
；Next basis
Binary hypersonic inlet is designed according to a conventional method, determines the geometric parameter of air intake duct,
With
；Then according to relational expression
Selection
；Finally according to formula（1）Calculate
Whether ensure that air intake duct carries out the normal geometry that becomes and adjusted, if it cannot be guaranteed that, reselect
Or reselect
With
, repeat above-mentioned design procedure..
The hypersonic working method for becoming geometry air intake duct of the binary, it is characterised in that when aircraft takes off from ground, makes air intake duct lip cover laminating compressing surface, and now air intake duct closes to protect engine.When flying speed is improved to relay point Mach number, air intake duct lip cover is set to be translated in face of direction of flow until intake duct starting.When free stream Mach number is further raised, retreat air intake duct lip cover, it is ensured that air intake duct realizes shock wave sealing state to ensure higher traffic capture.In normal range of operation, allow air intake duct lip cover as the reduction of speed of incoming flow is protracted along direction of flow or is retreated with the rise of speed of incoming flow along direction of flow, real-time ensuring air intake duct realizes that shock wave is sealed.
Operation principle of the present utility model is：Before scramjet engine reaches relay point Mach number, air intake duct needs to close to protect combustion chamber and other engine components.By will be moved after translatable lip cover, it is highly zero to make air intake duct isolator, and the air flow rate for now entering air intake duct is zero, and air intake duct is closed.When free stream Mach number reaches relay point Mach number, lip cover reach, air intake duct distance piece is highly gradually increased until that the separation bag of air intake duct contract section porch disappears, intake duct starting, and now air intake duct completes opening process regulation.When aircraft works in High Mach number（The upper limit of flight range）During state, the shock wave produced on air intake duct compression wedge surface is intersected in lip, and air intake duct realizes that optimal air-flow is captured and to the deceleration pressurization of air-flow.When flying speed increases, the shock wave wave angle produced on compressing surface reduces, now compression section in shock incidence air intake duct；In order to avoid the shock wave of compression section in incidence causes air-flow to separate and causes inlet characteristic to deteriorate, air intake duct lip cover is retreated, and shock wave is kept sealing state.When flying speed reduces, the shock wave wave angle increase produced on compressing surface, air intake duct produces overflow；In order to improve the traffic capture of air intake duct, lip cover extension makes shock wave keep sealing state.The high hypermutation geometry air intake duct of binary such as runs into that speed of incoming flow is too low or back-pressure many height in combustion chamber cause air intake duct inoperative, and translation lip cover reduces the contract ratio of air intake duct, can restart air intake duct.Cause pitot loss larger if air intake duct distance piece exit Mach number is too high, translation lip cover increase air intake duct contract ratio, effectively increase improves total pressure recovery coefficient to the deceleration pressurization of air-flow.
The utility model has the advantages that：Regulation of the binary hypersonic inlet from off state to opening only can be achieved with by the translation of simple lip cover, High Mach number state and low mach state contract than regulation and the regulation that captures of different inlet flow conditions down-offs.It is easy to realize, easy to control and ensure that air intake duct can obtain preferably synthetic aerodynamic performance in wider flight range.
Brief description of the drawings
Accompanying drawing 1, which is that binary is hypersonic, becomes geometry air intake duct schematic diagram；
Accompanying drawing 2 is to become geometry air intake duct off design point flow with contract than coupling regulation schematic diagram；
Accompanying drawing 3 is the region of accompanying drawing 2ⅠPartial enlarged drawing；
Accompanying drawing 4, which is that binary is hypersonic, becomes geometry air intake duct lip cover closed mode schematic diagram；
Accompanying drawing 5, which is that binary is hypersonic, becomes geometry Design of Inlet method flow diagram；
Accompanying drawing 6, which is that binary is hypersonic, becomes geometry air intake duct working method explanation；
Accompanying drawing 7 be determine geometry air intake duct it is inoperative/starting state flow field Mach number isopleth map（Containing streamline）；
Accompanying drawing 8 be become geometry air intake duct it is inoperative/starting state flow field Mach number isopleth map（Containing streamline）；
Accompanying drawing 9 is that fixed/change geometry Flow coefficient of inlet is contrasted with total pressure recovery coefficient；
Accompanying drawing 10 is that fixed/change geometry air intake duct distance piece exit Mach number is contrasted with pressure ratio；
Label title in figure：1. air intake duct compressing surface, 2. translatable lip cover, 3. air intake duct contract section, 4. air intake duct isolator, 5. the shock wave produced on combustion chamber cavity, 6. combustion chamber Gu Bi, 7. low mach incoming flow conditions air intake duct compressing surfaces, 8. multishock in the shock wave produced on High Mach number incoming flow conditions air intake duct compressing surface, 9. contracts section and isolator.
Embodiment
With reference to the accompanying drawings shown in 1, the hypersonic geometry air intake duct that becomes of the utility model binary is by compressing surface, and translatable lip cover, contract section and several parts of isolator are constituted, wherein translatable lip cover constitutes internal contraction tunnel and isolator passage with compressing surface.The compressing surface of air intake duct shown in 1 is three wedge compressing surfaces in figure, can be by air intake duct compression design into single wedge compressing surface during design, the mixing compressing surface that many wedge compressing surfaces, isentropic Compression face or wedge surface are combined with approximate isentropic Compression face, it is to optimize the key design parameter for obtaining air intake duct that it, which is acted on,
.The concrete form of compressing surface is given by corresponding type design task or aerial mission.The translatable lip cover afterbody of air intake duct in figure shown in 2 is overlapped with combustion chamber Gu Bi, using the moving direction of sliding motion sub-control lip cover, is single-degree-of-freedom movement.3 be air intake duct contract section in figure, the section outlet from inlet mouth to contract, and contract section aisle spare is gradually reduced.4 be air intake duct isolator in figure, and the air-flow of pressure fluctuation and the outlet of internal contraction section that isolator is used for isolating combustion chamber generation further slows down supercharging.5 be combustion chamber cavity in figure, and in combustion chamber, cavity entrance devises sudden expansion ledge structure.6 be combustion chamber Gu Bi in figure, and Gu Bi is connected with translatable lip cover using sliding motion pair.The moveable element of whole air intake duct only has translatable lip cover, and is only capable of doing single dof mobility translation.
With reference to the accompanying drawings shown in 2, when air intake duct works in low mach state, by translating lip cover in face of direction of flow, capture gas of overflow due to Angle of Shock Waves increase, increase flows into the throughput of air intake duct.During lip cover is translated, inlet mouth height and distance piece entrance height increase, and 7 be low mach state shock wave in figure, passes through the extension of lip cover, it is ensured that the road shock wave sealing of compressing surface the 3rd.8 be High Mach number state shock wave in figure, and the shock wave of High Mach number state compressing surface is sealed, it is ensured that air intake duct obtains optimal traffic capture.9 be the multishock in High Mach number state air intake duct contract section and isolator in figure.
With reference to the accompanying drawings shown in 3, pass through the combination of parameter shown in figure, it is possible to achieve air intake duct in translation motion contract than control.Specific method is as follows：It is parameter K to define the ratio between High Mach number state contract ratio and low mach state contract ratio, and air intake duct High Mach number state contract ratio is, low mach state contract ratio is
, according to the sign in figure, derive as follows：
（4）
Binary is hypersonic to become geometry Design of Inlet flow as shown in Figure 5.
Binary is hypersonic to become geometry air intake duct working method explanation as shown in Figure 6.
Application example
Application example 1：
1）Technical indicator：
Work range of Mach numbers：4.0~7.0
The Mach number upper limit that works is High Mach number 7.0, and the lower limit of working range is low mach 4.0, and design work state is Mach number 7.0.
2）Scheme is introduced：
With reference to Fig. 1, the high hypermutation geometry air intake ducts of wedge surface binary are compressed in design three, and three road compression wedge face angle degree are respectively 5o, 5.7o and 6.7o,
.Three roads compression wedge surface horizontal length is respectively 254.8 millimeters, 149.8 millimeters and 143.1 millimeters.Lip is to 120 millimeters of air intake duct bottom surface vertical height, air intake duct contract ratio during Mach 7.0
For 1.80, contract ratio during Mach number 4.0
For 1.64, Mach 7.0 and the air intake duct contract of Mach 4.0 than the ratio between K be 1.1.When free stream Mach number is 7.0, the road shock waves sealing of design three, when free stream Mach number reduction, in face of flowing the translatable lip cover of extension, it is ensured that the road shock wave of air intake duct the 3rd is sealed all the time.
In order to which comparative analysis becomes geometry air intake duct aeroperformance, geometric configuration on the basis of state during selection change geometry air intake duct Mach 7.0, in different free stream Mach numbers, lip cover is fixed all the time, and the hypersonic geometry air intake duct that becomes of binary is obtained with determining geometry air intake duct aeroperformance and being contrasted Numerical Simulation Results with becoming geometry air intake duct result by the method for numerical simulation.
3）Starting characteristic is contrasted：
From accompanying drawing 7 as can be seen that for the irremovable fixed geometry binary hypersonic inlet of lip cover, the contract ratio of air intake duct is remained in whole working range
.When free stream Mach number is since increase 0, it is necessary to increase to the ability normal starting of Mach 4.9, this Start mach number has been over the lower limit of normal range of operation, reduces the normal range of operation for air intake duct of knowing clearly；Protracted by lip cover along direction of flow, by the contract ratio of air intake duct from
It is down to
, by accompanying drawing 8 as can be seen that air intake duct Mach 3.4 can normal starting, air intake duct expands normal range of operation by the translation of lip cover, it is ensured that the preferable starting performance of air intake duct.
4）Aeroperformance is contrasted：
Accompanying drawing 9 be binary it is hypersonic become geometry air intake duct and determine geometry air intake duct range of Mach numbers into 4.0~7.0 Numerical Simulation Comparative result, in figure
For Flow coefficient of inlet,
For inlet total pres sure recovery coefficient.As can be seen that two kinds of Flow coefficient of inlet increase with the increase of Mach number, total pressure recovery coefficient is reduced with the increase of Mach number.By translating lip cover under low mach inlet flow conditions, it is ensured that the 3rd road shock wave sealing, become geometry Flow coefficient of inlet apparently higher than determining geometry air intake duct, total pressure recovery coefficient is also above determining geometry air intake duct value under identical inlet flow conditions.Free stream Mach number is lower, and the aeroperformance advantage for becoming geometry air intake duct is more obvious.When free stream Mach number determines that geometry air intake duct is high by 9% for 4.0 time-varying geometry inlet total pres sure recovery coefficient ratios, discharge coefficient is high by 21%.During accompanying drawing 10 is the contrast of air intake duct distance piece exit Mach number and pressure ratio, figure
Distance piece exit Mach number is represented,Represent inlet compression ratio.As can be seen that with the increase of free stream Mach number, the distance piece exit Mach number and pressure ratio of air intake duct increase, and two kinds of air intake duct variation tendencies are basically identical.Under the inlet flow conditions less than design point Mach number 7.0, due to determining the contract ratio that geometry air intake duct remains higher, and become geometry air intake duct translation lip cover and reduce contract ratio, cause change geometry air intake duct to be slightly below the deceleration pressurization of air-flow and determine geometry air intake duct, become geometry air intake duct distance piece exit Mach number slightly higher, pressure ratio is lower slightly, but has no effect on air intake duct and normally effectively work.
Claims (1)
1. a kind of binary is hypersonic to become geometry air intake duct, by compressing surface, air intake duct contract section, isolator and lip cover composition；It is characterized in that：Above-mentioned lip cover is can be along direction of flow anterior-posterior translation formula structure；And the geometric parameter of air intake duct meets below equation
（1）
Wherein K is the ratio between High Mach number contract ratio and low mach contract ratio in air intake duct normal range of operation；
For air intake duct High Mach number contract ratio, the i.e. upper limit of normal range of operation,
For air intake duct low mach contract ratio, the i.e. lower limit of normal range of operation,
WithIt is given by specific aerial mission；
The distance of low mach state translation is moved to from High Mach number state for air intake duct lip cover,
For High Mach number state air intake duct contract section outlet height,For High Mach number state air intake duct contract section entrance height；For air intake duct contract section porch compressing surface and the angle of horizontal direction,
For air intake duct isolator and the angle of horizontal direction.
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| CN 201220233265 CN202628279U (en) | 2012-05-23 | 2012-05-23 | Binary hypersonic speed-variable geometric air inlet channel |
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| Application Number | Priority Date | Filing Date | Title |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102705081A (en) * | 2012-05-23 | 2012-10-03 | 南京航空航天大学 | Binary hypersonic variable geometrical inlet channel, design method and work mode |
| CN103939217A (en) * | 2014-04-18 | 2014-07-23 | 南京航空航天大学 | Hypersonic variable-geometry air inlet channel with rectangular section, design method and work mode |
| CN104015926A (en) * | 2014-05-13 | 2014-09-03 | 南京航空航天大学 | Implication type cover hood abandoning scheme for hypersonic aircraft |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN105240160A (en) * | 2015-10-29 | 2016-01-13 | 西北工业大学 | Variable structure combustion chamber of rocket-based-combined-cycle engine |
| CN105571810A (en) * | 2016-01-28 | 2016-05-11 | 南京航空航天大学 | Translational inner-parallel combined power air intake channel mode conversion device and translational inner-parallel combined power air intake channel mode conversion method |
| CN108088679A (en) * | 2016-11-23 | 2018-05-29 | 北京机电工程研究所 | Two dimensional inlet experimental rig |
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2012
- 2012-05-23 CN CN 201220233265 patent/CN202628279U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102705081A (en) * | 2012-05-23 | 2012-10-03 | 南京航空航天大学 | Binary hypersonic variable geometrical inlet channel, design method and work mode |
| CN103939217A (en) * | 2014-04-18 | 2014-07-23 | 南京航空航天大学 | Hypersonic variable-geometry air inlet channel with rectangular section, design method and work mode |
| CN103939217B (en) * | 2014-04-18 | 2016-03-02 | 南京航空航天大学 | Rectangular cross-section hypersonic change geometry intake duct and design method and working method |
| CN104015926A (en) * | 2014-05-13 | 2014-09-03 | 南京航空航天大学 | Implication type cover hood abandoning scheme for hypersonic aircraft |
| CN104015926B (en) * | 2014-05-13 | 2017-01-04 | 南京航空航天大学 | Scheme abandoned by hypersonic aircraft connection formula calotte |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN105240160A (en) * | 2015-10-29 | 2016-01-13 | 西北工业大学 | Variable structure combustion chamber of rocket-based-combined-cycle engine |
| CN105571810A (en) * | 2016-01-28 | 2016-05-11 | 南京航空航天大学 | Translational inner-parallel combined power air intake channel mode conversion device and translational inner-parallel combined power air intake channel mode conversion method |
| CN105571810B (en) * | 2016-01-28 | 2017-04-19 | 南京航空航天大学 | Translational inner-parallel combined power air intake channel mode conversion device and translational inner-parallel combined power air intake channel mode conversion method |
| CN108088679A (en) * | 2016-11-23 | 2018-05-29 | 北京机电工程研究所 | Two dimensional inlet experimental rig |
| CN108088679B (en) * | 2016-11-23 | 2019-08-13 | 北京机电工程研究所 | Two dimensional inlet experimental rig |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121226 Termination date: 20150523 |
|
| EXPY | Termination of patent right or utility model |