CN104727944A - Structure of rocket-based-combined power engine capable of broadening working range of fixed-geometry air inlet channel - Google Patents
Structure of rocket-based-combined power engine capable of broadening working range of fixed-geometry air inlet channel Download PDFInfo
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- CN104727944A CN104727944A CN201510025619.2A CN201510025619A CN104727944A CN 104727944 A CN104727944 A CN 104727944A CN 201510025619 A CN201510025619 A CN 201510025619A CN 104727944 A CN104727944 A CN 104727944A
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- air bleed
- bleed slot
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- intake duct
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Abstract
The invention relates to a structure and a method of a rocket-based-combined power engine capable of broadening a working range of a fixed-geometry air inlet channel. A rectangular air bleed groove along a flow direction is formed in a compressed surface of a top plate in an area in which an internal pressure section separating packet can exist; the long side of the air bleed groove is parallel to the airflow direction; the separating packet is released to realize throughflow of an air inlet channel, so that the working range of the air inlet channel is expanded; the problems that when a high-hypersonic air inlet channel works below the mach number of a relay point to a low hypersonic state, the power engine is not started in general, a relatively large separating packet is generated on one side of the top plate of the internal pressure section, the flow field is complicated in structure and the performance is seriously reduced are solved; the working range of the fixed-geometry air inlet channel is greatly broadened; normal work of the air inlet channel below the mach number of the relay point is realized; and the lowest work mach number of the air inlet channel is reduced to be not greater than 2.0.
Description
Technical field
The present invention relates to a kind of rocket base assembly power motor and widen the structure and method of determining geometry intake duct operating range, when free stream Mach number is significantly less than intake duct self-starting Mach number, realizes intake duct by the method and normally work.
Background technique
Rocket base assembly power motor (RBCC), is merged by rocket motor and pressed engine and forms, taken into account the advantage of these two kinds of motors, and being expected to will become the ideal power of a kind of new earth to orbit and return transportation system of alternative rocket in future.Hypersonic inlet, as one of the critical component of this motor, must become the key technology that need capture as early as possible.
Current hypersonic inlet is generally mixed pressure formula.Mixed compression inlet has interior pressure section, thus causes it to there is starting problem.When free stream Mach number is less than its self-starting Mach number, intake duct is inoperative, there is large size and is separated, performance degradation in flow field.Starting problem limits the work range of Mach numbers of intake duct.
Along with the iterative method of RBCC reseach of engine, require that intake duct also can normally work under extremely low Mach number, this is just badly in need of a kind of method effectively widening intake duct operating range, thus punching module can be made to produce thrust under lower Mach number, to improve engine performance, guarantee that RBCC motor has higher Economy in very large operating envelope.
At present, the operating range of hypersonic inlet mainly in Ma4 ~ 7+, its turn of level Mach number at about Ma4, therefore during Design of Inlet general minimum work Mach number a little less than Ma4.In order to realize Ma4 self-starting, many employings groove is assisted to air bleed slot (air bleed slot is vertical with airflow direction), as document 1: Liu Yuan, Jin Zhiguang, open Kun unit, etc. the Analysis on Design Parameters of hypersonic inlet self adaption gas pressure relief slot. aviation power journal .2013.23 (6): 1313-1321.; Document 2: Zhang Xiaojia, Yue Lianjie, Zhang Xinyu. imperial palace contraction ratio binary hypersonic inlet wave system configuration feature. Push Technology .2012.33 (4): 505-509.; Document 3: He Yongjie, Ma Gaojian, Liu Zhiwei. let out except improving the technique study determining geometry mixed compression inlet performance by boundary layer. airborne weapon .2010..This air bleed slot set-up mode is widely used.Being different from this mode, document 4: south orientation army, a Kun unit, Jin Zhiguang, Li Yongzhou. rectangle turns the analysis of circular intake duct Mach 5 positive 8 ° of angle of attack startabilities. Nanjing Aero-Space University's journal, 2012,44 (2): 146-151..Have employed the air bleed slot (air bleed slot is parallel with airflow direction) along flowing to, to realize intake duct at High Mach number, the starting of large attack angle state.
For hypersonic inlet, air bleed slot is generally used for and realizes relay point self-starting and improve flow field.Along with the propelling of RBCC reseach of engine, require that intake duct can stability and high efficiency work in scope large as far as possible.This just require hypersonic inlet below relay point very on a large scale in also can normally work.At present, realize by air bleed slot the method that intake duct lower work threshold greatly expands rarely seen in open source literature.
When hypersonic inlet works in relay point Mach number with down to very low ultrasound velocity state, generally inoperative.Interior pressure section top board side produces larger separation bag, and flow field structure is complicated, performance degradation.
Summary of the invention
The technical problem solved
In order to avoid the deficiencies in the prior art part, the present invention proposes a kind of rocket base assembly power motor and widens the structure and method of determining geometry intake duct operating range, by be separated in interior pressure section wrap the region that may exist top board compressing surface on open rectangle air bleed slot along flowing to, its long limit is parallel with airflow direction, bleed off separation bag through-flow to realize intake duct, thus expand the operating range of intake duct.
Technological scheme
The structure of determining geometry intake duct operating range widened by a kind of rocket base assembly power motor, it is characterized in that: the top board compressing surface that the section of pressure is separated bag domain of the existence in the hypersonic inlet of rocket base assembly power motor is opened the rectangle air bleed slot along flowing to, the long limit of rectangle air bleed slot is parallel with airflow direction.
The structure of determining geometry intake duct operating range widened by rocket base assembly power motor, it is characterized in that: the top board compressing surface that the section of pressure is separated bag domain of the existence in the hypersonic inlet of rocket base assembly power motor is opened the rectangle air bleed slot along flowing to, the long limit of rectangle air bleed slot is parallel with airflow direction.
The most leading edge of described rectangle air bleed slot corresponds to and is separated bag leading edge or lip shock and top board intersection location, and trailing edge corresponds to and is separated bag trailing edge or lip shock and top board intersection location.
Described rectangle air bleed slot width W
b≤ 10mm, rectangle air bleed slot number n=(0.2 ~ 0.5) (W/W
b), round; Wherein: W is that intake duct is wide.
Described rectangle air bleed slot and top board place angle α <90 °.
Realize the method weighing described arbitrary structure, it is characterized in that step is as follows:
Step 1: according to the normal range of operation of the intake duct that designing requirement is determined, adopts the method for numerical simulation analysis to determine to be separated the position of bag;
Step 2: open the rectangle air bleed slot along flowing on the top board compressing surface being separated bag domain of the existence, the long limit of rectangle air bleed slot is parallel with airflow direction; The most leading edge of described rectangle air bleed slot corresponds to and is separated bag leading edge or lip shock and top board intersection location, and trailing edge corresponds to and is separated bag trailing edge or lip shock and top board intersection location; The width W of described rectangle air bleed slot
b≤ 10mm, rectangle air bleed slot number n=(0.2 ~ 0.5) (W/W
b), round; Described rectangle air bleed slot and top board place angle α <90 °.
Beneficial effect
A kind of rocket base assembly power motor that the present invention proposes widens the structure and method of determining geometry intake duct operating range, by be separated in interior pressure section wrap the region that may exist top board compressing surface on open rectangle air bleed slot along flowing to, its long limit is parallel with airflow direction, bleed off separation bag through-flow to realize intake duct, thus expand the operating range of intake duct.Solve when hypersonic inlet works in relay point Mach number with down to very low ultrasound velocity state, generally inoperative.Interior pressure section top board side produces larger separation bag, flow field structure is complicated, and the problem of performance degradation, greatly widens the operating range of determining geometry mixed compression inlet, realize intake duct normally to work below relay point Mach number, and the minimum work Mach number of intake duct is down to less than 2.0.
The present invention's beneficial effect is compared with prior art:
1, along the air bleed slot flowed to, there is very large adaptability, greatly can reduce the minimum work Mach number of intake duct.
2, the method is not by the restriction of intake duct geometrical shape, can be applicable to various types of mixed compression inlet.
Accompanying drawing explanation
Fig. 1: be the air bleed slot structural representation along the flow direction that a mixed compression inlet is arranged
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
The embodiment of the present invention:
For certain hypersonic inlet, suppose self-starting Mach 2 ship 4.0, expand its operating range downwards, be low to moderate Ma2.0 most.Intake duct is separated the region of bag existence or the region (if partial status is without being separated, adopting the latter) of inlet lip shock wave and top board intersection location on the scope inside ceiling panel of Ma2.0 ~ 4.0 to adopt CFD to predict.
Arrange air bleed slot in this region, its most leading edge corresponds to Ma2.0 state and is separated bag leading edge or lip shock and top board intersection location.Its trailing edge corresponds to Ma4.0 state and is separated bag trailing edge or lip shock and top board intersection location.
Determine air bleed slot width W
b≤ 10mm, air bleed slot number n=(0.2 ~ 0.5) (W/W
b), round.Non-rectangular cross-section press curve Size calculation.
Determine air bleed slot passage and top board place angle α, generally get α <90 °.
Controlled in order to realize discharge quantity, also air bleed slot switch can be set.Under the prerequisite that intake duct normally works, reduce air bleed slot aisle spare, improve inlet characteristic.Rule adjusting is determined by wind tunnel test.
Specific embodiment is as follows:
Fig. 1 is the application example that a binary determines geometry mixed compression inlet, for convenience of display, only shows half-breadth.1 is inlet lip plate, and 2 is intake duct top board, and 3 is the air bleed slot (being 3 roads in figure) of design, and 4 is the angle of bleed passage and top board.
1, determine geometry binary mixed compression inlet for one, design is along the air bleed slot flowed to.This Design of Inlet point is Ma6, normally can work within the scope of Ma4-7, self-starting Mach 2 ship 4.The long 1600mm of intake duct, interior pressure segment length 390mm, width is 230mm.Side plate is sweepforward configuration.
2, by numerical simulation analysis, when free stream Mach number is in Ma2 ~ 4 scope, intake duct is inoperative.Be separated bag and be positioned at pressure section, in distance leading edge 1300 ~ 1600mm region.Air bleed slot is set in this region, air bleed slot width W for this reason
bbe taken as 10mm, because the wide W of intake duct is 230mm, after calculating, determine uniform 6 road air bleed slots side by side.Air bleed slot runner and top board angle α are taken as 26 °.
Numerical simulation shows, after arranging air bleed slot, intake duct normally can work in the scope of Ma1.5 ~ 4, thus successfully widens intake duct operating range to Ma1.5 ~ 7.
Claims (5)
1. the structure of determining geometry intake duct operating range widened by a rocket base assembly power motor, it is characterized in that: the top board compressing surface that the section of pressure is separated bag domain of the existence in the hypersonic inlet of rocket base assembly power motor is opened the rectangle air bleed slot along flowing to, the long limit of rectangle air bleed slot is parallel with airflow direction.
2. the structure of determining geometry intake duct operating range widened by rocket base assembly power motor according to claim 1, it is characterized in that: the most leading edge of described rectangle air bleed slot corresponds to and is separated bag leading edge or lip shock and top board intersection location, trailing edge corresponds to and is separated bag trailing edge or lip shock and top board intersection location.
3. the structure of determining geometry intake duct operating range widened by rocket base assembly power motor according to claim 1, it is characterized in that: described rectangle air bleed slot width W
b≤ 10mm, rectangle air bleed slot number n=(0.2 ~ 0.5) (W/W
b), round; Wherein: W is that intake duct is wide.
4. the structure of determining geometry intake duct operating range widened by rocket base assembly power motor according to claim 1, it is characterized in that: described rectangle air bleed slot and top board place angle α <90 °.
5. realize a method for arbitrary structure described in Claims 1 to 4, it is characterized in that step is as follows:
Step 1: according to the normal range of operation of the intake duct that designing requirement is determined, adopts the method for numerical simulation analysis to determine to be separated the position of bag;
Step 2: open the rectangle air bleed slot along flowing on the top board compressing surface being separated bag domain of the existence, the long limit of rectangle air bleed slot is parallel with airflow direction; The most leading edge of described rectangle air bleed slot corresponds to and is separated bag leading edge or lip shock and top board intersection location, and trailing edge corresponds to and is separated bag trailing edge or lip shock and top board intersection location; The width W of described rectangle air bleed slot
b≤ 10mm, rectangle air bleed slot number n=(0.2 ~ 0.5) (W/W
b), round; Described rectangle air bleed slot and top board place angle α <90 °.
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| CN201510025619.2A CN104727944A (en) | 2015-01-19 | 2015-01-19 | Structure of rocket-based-combined power engine capable of broadening working range of fixed-geometry air inlet channel |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105221266A (en) * | 2015-10-29 | 2016-01-06 | 西北工业大学 | A kind of rocket based combined cycle motor becomes absorbs control intake duct |
| CN106021831A (en) * | 2016-07-26 | 2016-10-12 | 厦门大学 | Design method of self-adaptive communication reverse reflux tank air inflow channel |
| CN106907272A (en) * | 2017-03-23 | 2017-06-30 | 西北工业大学 | Structure changes Rocket based combined cycle engine |
| CN108412618A (en) * | 2018-04-17 | 2018-08-17 | 中国人民解放军国防科技大学 | Hypersonic/supersonic axisymmetric inlet lip and design method thereof |
| CN110805495A (en) * | 2019-12-05 | 2020-02-18 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
| CN113107681A (en) * | 2021-04-21 | 2021-07-13 | 南京航空航天大学 | Continuously adjustable air inlet duct air bleeding device |
| CN113107680A (en) * | 2021-04-21 | 2021-07-13 | 南京航空航天大学 | Hypersonic-speed high-internal-contraction-ratio air inlet channel with stepless adjustable air release valve and control method |
| CN113323756A (en) * | 2021-06-22 | 2021-08-31 | 西安航天动力研究所 | Double-flow-passage graded adjustable wide-range air inlet passage, engine and air inlet adjusting method |
| CN114263533A (en) * | 2021-12-20 | 2022-04-01 | 中国人民解放军国防科技大学 | Shock wave/boundary layer interference control device based on secondary flow circulation array and self-adaptive control method |
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| WO1999033701A2 (en) * | 1997-12-29 | 1999-07-08 | Vladimir Timofeevich Medvedev | Self-adjusting air intake |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105221266A (en) * | 2015-10-29 | 2016-01-06 | 西北工业大学 | A kind of rocket based combined cycle motor becomes absorbs control intake duct |
| CN106021831A (en) * | 2016-07-26 | 2016-10-12 | 厦门大学 | Design method of self-adaptive communication reverse reflux tank air inflow channel |
| CN106021831B (en) * | 2016-07-26 | 2018-11-13 | 厦门大学 | Adaptive connection reverse backflow slot Design of Inlet method |
| CN106907272A (en) * | 2017-03-23 | 2017-06-30 | 西北工业大学 | Structure changes Rocket based combined cycle engine |
| CN108412618A (en) * | 2018-04-17 | 2018-08-17 | 中国人民解放军国防科技大学 | Hypersonic/supersonic axisymmetric inlet lip and design method thereof |
| CN110805495A (en) * | 2019-12-05 | 2020-02-18 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
| CN113107681A (en) * | 2021-04-21 | 2021-07-13 | 南京航空航天大学 | Continuously adjustable air inlet duct air bleeding device |
| CN113107680A (en) * | 2021-04-21 | 2021-07-13 | 南京航空航天大学 | Hypersonic-speed high-internal-contraction-ratio air inlet channel with stepless adjustable air release valve and control method |
| CN113107681B (en) * | 2021-04-21 | 2022-02-08 | 南京航空航天大学 | Continuously adjustable air inlet duct air bleeding device |
| CN113323756A (en) * | 2021-06-22 | 2021-08-31 | 西安航天动力研究所 | Double-flow-passage graded adjustable wide-range air inlet passage, engine and air inlet adjusting method |
| CN114263533A (en) * | 2021-12-20 | 2022-04-01 | 中国人民解放军国防科技大学 | Shock wave/boundary layer interference control device based on secondary flow circulation array and self-adaptive control method |
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Application publication date: 20150624 |
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