CN113788151A - Hypersonic-speed air inlet channel forced transition method based on macro-pore structure - Google Patents
Hypersonic-speed air inlet channel forced transition method based on macro-pore structure Download PDFInfo
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- 238000009434 installation Methods 0.000 claims abstract description 9
- 238000004088 simulation Methods 0.000 claims description 10
- 238000013461 design Methods 0.000 claims description 3
- 238000002474 experimental method Methods 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 claims 1
- 238000012545 processing Methods 0.000 abstract description 10
- 239000000463 material Substances 0.000 description 6
- 239000002131 composite material Substances 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
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- 229910003460 diamond Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
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- Aviation & Aerospace Engineering (AREA)
- Aeration Devices For Treatment Of Activated Polluted Sludge (AREA)
Abstract
A method for forced transition of a hypersonic-speed air inlet channel based on a macro-pore structure comprises the following steps: 1) the macro pore structure is formed by arranging and distributing a plurality of rows of concave cavity units in a staggered manner along the flow direction, and the size of the macro pore structure is determined; 2) determining the installation position of the macro-pore structure on the surface of the air inlet along the flow direction and meeting the following three conditions: ensuring that the macro-pore structure is arranged in a smooth and flat area of the surface of the air inlet channel; a sufficient distance should be kept between the last row of cavity units and the outlet position of the air inlet channel; the mounting direction of the concave cavity unit is vertical to the incoming flow direction; 3) and determining the length of the macro-pore structure along the spanwise direction of the air inlet and the row number of the concave cavity units. Compared with the outward convex shape of the conventional diamond-shaped and backswept slope-shaped transition device, the macro pore structure is of an inward concave shape, and the transition device has the advantages of small flow loss, simplicity in processing, no change of the area of a flow channel, good transition effect and the like.
Description
Technical Field
The invention relates to the field of forced transition of an air inlet channel, in particular to a forced transition method of a hypersonic-speed air inlet channel based on a macro pore structure.
Background
The aircraft air inlet is used as a component of a power system and mainly used for supplying air with a certain flow rate to an engine and ensuring that an air inlet flow field can meet the requirement of normal operation of an air compressor and a combustion chamber. Relevant flight tests show that the boundary layer of the compression surface of the air inlet channel of the air-breathing hypersonic aircraft is usually in a laminar state, and the air inlet channel cannot be guaranteed to work according to an expected design state. Therefore, a forced transition device is usually installed on the compression surface of the inlet precursor to obtain turbulent flow so as to ensure the normal operation of the engine.
At present, the method is widely applied and has a diamond-shaped and sweepback slope-shaped forced transition method. Researches find that the two transition methods can induce and generate a series of vortex pairs moving along the flow direction in the boundary layer so as to rapidly trigger the transition of the boundary layer, and the forced transition methods are widely applied to hypersonic flight vehicles such as X-43A, X-51A and HIFire.
At the present stage, diamond type and sweepback slope type forced transition methods used for hypersonic aircraft are both outwards convex, excessive materials needing to be cut off are more during actual processing, not only can materials be wasted, but also processing time is long, wherein the sweepback slope type forced transition device is in an irregular pentagonal shape, and actual processing is difficult. In addition, the convex shape can reduce the flow passage area, reduce the air intake quantity of the engine and reduce the thrust of the engine.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides a hypersonic air inlet channel forced transition method based on a macro-pore structure, wherein the macro-pore structure is formed by arranging a plurality of rows of transition units back and forth along the flow direction.
In order to achieve the purpose, the invention adopts the following technical scheme:
the transition unit is formed by linearly distributing a plurality of cubic cavity units on the surface of the material, and the relative positions of the front and rear rows of cavities are in a staggered distribution form.
The material can be a metal material or a braided composite material. The material can bear the heat generated by the mutual friction between the aircraft and the air without deformation and is easy to machine a concave cavity structure on the surface, and if the material is a woven composite material, the concave cavity structure is easy to weave on the surface.
The dimensions of the cubic cavity are determined by three values, respectively: the length a, the width d and the depth h, and the values of a, d and h are all between 1mm and 2 mm.
The staggered distribution pattern is determined by three values, respectively: the radial distance u between adjacent cavities in the same row, the flow direction distance v between two rows of adjacent cavities in the front and back, and the offset distance w between the adjacent cavities in the front and back. u and v both take on the values of 1mm to 2mm, and w takes on the value of
The specific size is selected according to actual requirements and test results, comprehensively considering transition effects, transition positions, thermal protection, structural strength, processing and manufacturing and other factors.
An air inlet forced transition method based on a macro pore structure comprises the following implementation steps:
1. determining the structural size of the macro-pore, namely six values of a, d, h, u, v and w of the cavity unit of the macro-pore structure.
(1) Firstly, determining three dimensions of the length a, the width d and the depth h of the cavity unit;
the values of a, d and h are accurately designed, the values can be corrected through results obtained through numerical simulation or experiments, the numerical simulation can reflect the transition effect of the cavity unit through the value of the intermittent factor gamma obtained through a gamma-Re theta t model, and the transition effect is better when the change amount of the gamma value is larger after the same length flows. The size of the cavity which meets the transition effect under the design working condition is determined according to the conditions.
(2) Determining the spanwise distance u between adjacent cavities in the same row;
the value of the span-wise distance u between the cavities should not be larger than the width d of the cavity unit, so as to ensure that all laminar flows in the flow direction can be transitioned, and the value is as small as possible based on the current processing technology and the manufacturing level. After the width d and the spanwise distance u are determined, the offset distance between the front concave cavity and the rear concave cavity can be obtained
(3) Determining the flow direction distance v between two adjacent rows of cavities;
the flow direction distance v is selected to be a small value as much as possible, the maximum value of the flow direction distance v does not exceed the length a of the cavity unit, and the flow direction distance v is selected according to the actual transition effect and the processing level.
2. And determining the installation position of the macro-pore structure on the surface of the air inlet along the flow direction.
The mounting position of the cavities in the macro-pore structure should simultaneously satisfy the following conditions:
(1) the forced transition device is arranged in the area with a smooth and flat surface. In order to obtain a good transition effect of the macro-pore structure, the number of the arranged cavity rows must reach a certain amount, and the minimum value of the length range of the flowing cavity is recommended to be larger than 5 disturbance wavelength ranges. The method for calculating the disturbance wavelength adopts a gamma-Re theta t transition model based on local variables of a flow field, and determines the disturbance wavelength by carrying out numerical simulation on an air inlet channel.
(2) The last row of cavities should be kept at a sufficient distance from the inlet exit, i.e. it should be ensured that the length of the cavities in the flow direction should be below a maximum. The maximum value of the cavity length is determined as follows: in a state where transition is least likely to occur (the state where transition is least likely to occur is determined according to the flight mach number, the flight altitude, the attack angle, and the wall temperature), an intermittent factor γ value is obtained according to a γ -Re θ t transition model simulation, when all the boundary layer at the inlet port exit is dominated by a high γ value (greater than 0.95), the transition process is completed, and at this time, the flow direction position where γ ═ 0.95 is the maximum value point of the cavity length.
(3) The mounting direction of the concave cavity is vertical to the incoming flow direction: the macro pore structure is arranged in the direction vertical to the incoming flow, so that the rear flow field is uniformly distributed, and the processing of the macro pore structure is facilitated.
3. And determining the length of the macro-pore structure along the spanwise direction of the air inlet and the row number of the concave cavity units.
Taking a binary inlet as an example, it is proposed to arrange a macro-pore structure along the spanwise direction of the inlet, and the number of rows of cavities along the flow direction can also be determined by the flow direction distance v and the length a of the cavity unit. The larger the number of the cavity rows, the better the overall transition effect, but the number of the cavity rows should be properly selected in combination with the space structure.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
compared with the outward convex shape of the conventional diamond-shaped and sweepback slope-shaped transition device, the hypersonic air inlet passage forced transition method based on the macro pore structure is characterized in that the macro pore structure is in an inward concave shape and is hidden in the inner wall of the air inlet passage, the transition device in the form can not change the flow area of a flow passage, and the transition device can be triggered in advance and can ensure that the flow of the engine air inlet is not reduced due to the existence of the transition device. In addition, the transition device designed by the hypersonic air inlet channel forced transition method based on the macro-pore structure is simple to process, and only a plurality of rows of counter bores need to be processed on the inner wall of the air inlet channel, so that the transition device has the advantages of small flow loss, good transition effect and the like.
Drawings
Fig. 1 is a schematic structural diagram of a macro-pore structure cavity unit manufactured according to an embodiment of the present invention.
Fig. 2 is a schematic view of the distribution of macro-void structure cavity units on a surface to be mounted according to an embodiment of the present invention.
Fig. 3 shows the variation of the pause factor γ in the flow direction with the length of the flow through, which is obtained by numerical simulation, in the boundary layer of the macro-pore structure made by the embodiment of the present invention.
FIG. 4 is a schematic diagram of a hypersonic inlet duct in accordance with an embodiment of the present invention.
Fig. 5 is an axial view (partially) of the mounting position of the air inlet of the macro-pore structure manufactured by the embodiment of the invention.
Fig. 6 is a schematic (partial) right view of the installation position of the macro-pore structure in the air inlet according to the embodiment of the present invention.
In fig. 1 to 6, each symbol represents:
a. the length of the cavity unit; d. the width of the cavity unit; h. the depth of the cavity unit; u. the spanwise distance between adjacent cavities in the same row; v, flow direction distance between two adjacent rows of cavities in the front and the back; w. offset distance between adjacent cavities in front and back; 1. a cavity unit of macro-pore structure; 2. the inner wall surface of the hypersonic air inlet channel; 3. the outer wall surface of the hypersonic inlet channel; 4. a central cone; 5. an air inlet casing; a pause factor derived from a gamma-Re θ t model; l/a ratio of the length L of the point of the surface of the inclined plate from the foremost end of the inclined plate to the length a of the cavity unit.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects of the present invention clearer and clearer, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.
Referring to fig. 1 to 6, in the method for a high supersonic speed air inlet forced transition in this embodiment, a cavity unit of a macro pore structure is used as a basic unit for triggering transition, see fig. 1. The rows of cavity units 1 are distributed in a staggered manner to form a macro-pore structure, as shown in fig. 2.
The specific implementation mode comprises the following steps:
1. combining the actual requirements and the results obtained by numerical simulation, the cavity unit 1 is designed into a cubic structure with the length a, the width d and the depth h of 2 mm.
2. And selecting the number of the cavity rows and the distribution form of the macro pore structure according to the space size of the actual installation position. In this embodiment, the spanwise distance u between adjacent cavities in the same row is 2mm, the flow direction distance v between two adjacent rows of cavities is 1mm, and the offset distance between adjacent cavity units is defined by
Which can be seen as 2mm, the number of rows of cavities is 5.
3. The surface of the hypersonic air inlet comprises an inner wall surface 2 of the hypersonic air inlet and an outer wall surface 3 of the hypersonic air inlet at the selected installation position of the surface of the hypersonic air inlet. A macro-pore structure is arranged on the inner wall surface 2 of the hypersonic air inlet, the local area of the arrangement can be simplified into an inclined plate, the simplified axonometric view is shown in figure 5, and the right view is shown in figure 6. In the present embodiment, the macro-pore structure is installed at a distance of 60mm from the inlet of the intake duct, i.e., L/a is 30 in fig. 3, where L/a represents the ratio of the length L of a point of the surface of the swash plate from the foremost end of the swash plate to the length a of the pocket unit, and the dimensionless number represents the distance through which the air stream flows. As can be seen from fig. 3, there is a large increase in the gamma value (the pause factor derived from the gamma-Re θ t model) from about 0.03 to 0.23 in increments of 0.2 as the gas stream flows through the region where the macro-pore structure is located (30< L/a < 42). When the airflow is at the position where L/a >120, the value of γ is already greater than 0.95, and transition is considered to be completed at L/a ═ 120. It can be concluded from fig. 3 that when the distance between the rear end of the installation position of the macro-pore structure and the outlet position of the air inlet channel is not less than 156mm, the airflow can meet the requirements of the rear component on the flow field after forced transition.
4. And processing a macro pore structure on the surface of the selected part. In the present embodiment, the hypersonic inlet profile is applied as shown in fig. 4, and a macro-pore structure is installed on the surface of the central cone 4 and the inner surface of the inlet casing 5. 5 rows of concave cavity units are distributed in a staggered mode to form a macro-pore structure, and the bottoms of the concave cavity units are parallel to the inner wall face of the hypersonic-speed air inlet channel. Because the macro-pore structure is manufactured on the inner wall surface of the hypersonic air inlet channel, the effect of forced transition of the air flow flowing through the air inlet channel is achieved.
In practical applications, the installation range of the forced transition device on the inner wall surface of the hypersonic air inlet channel should be determined according to the minimum distance between the forced transition device and the outlet position of the air inlet channel and the structural installation space of the hypersonic air inlet channel. The mounting mode can be realized by mounting a prefabricated macro-pore structure plate on the inner wall surface of the hypersonic air inlet channel through riveting and the like, and a concave cavity unit can also be directly processed on the air inlet channel main body. When the right-angle structure of the cavity unit is processed, the right-angle part can be properly rounded based on the existing processing technology.
Claims (8)
1. A method for forced transition of a hypersonic-speed air inlet channel based on a macro-pore structure is characterized by comprising the following steps:
1) the macro pore structure is formed by arranging and distributing a plurality of rows of concave cavity units in a staggered manner along the flow direction, and the size of the macro pore structure is determined;
2) determining the installation position of the macro-pore structure on the surface of the air inlet along the flow direction and meeting the following three conditions: ensuring that the macro-pore structure is arranged in a smooth and flat area of the surface of the air inlet channel; a sufficient distance should be kept between the last row of cavity units and the outlet position of the air inlet channel; the mounting direction of the concave cavity unit is vertical to the incoming flow direction;
3) and determining the length of the macro-pore structure along the spanwise direction of the air inlet and the row number of the concave cavity units.
2. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in the step 1), three dimensions of the length a, the width d and the depth h of the cavity unit are determined: the length a, the width d and the depth h of the cavity unit are corrected through results obtained through numerical simulation or experiments, the transition effect of the cavity unit can be reflected by the value of the intermittent factor gamma obtained through a gamma-Re theta t model through the numerical simulation, the transition effect is better when the change amount of the gamma value is larger after the same length flows through, and the cavity size meeting the transition effect under the design working condition is determined through the conditions.
3. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 2, characterized in that: the length a, the width d and the depth h of the cavity unit are 1-2 mm and are consistent.
4. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 2, characterized in that: in the step 1), determining the spanwise distance u between adjacent cavities in the same row: the value of the spreading distance u between the adjacent cavities in the same row is not larger than the width d of the cavity unit so as to ensure that all laminar flows in the flowing direction can be twisted, and then the offset distance between the front cavity and the rear cavity is determined
5. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 2, characterized in that: in the step 1), determining the flow direction distance v between two adjacent rows of cavities: the flow direction distance v between the adjacent front and back rows of cavities does not exceed the length a of the cavity unit.
6. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in the step 2), the minimum value of the length range of the flow direction cavity is larger than 5 disturbance wavelength ranges, and the calculation method of the disturbance wavelength adopts a gamma-Re theta t transition model based on local variables of the flow field and determines through numerical simulation of the air inlet channel.
7. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in step 2), the maximum value of the length of the cavity along the flow direction is determined as follows: in a state where transition is least likely to occur, an intermittent factor γ value is obtained according to γ -Re θ t transition model simulation, and when all the boundary layers at the outlet of the air intake channel are dominated by a high γ value, the transition process is completed, and a flow position where γ is 0.95 is a maximum value point of the cavity length.
8. The hypersonic air inlet channel forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in the step 3), the macro-pore structures are all arranged along the expanding direction of the air inlet, the number of the cavity rows along the flowing direction is determined by the flowing direction distance v and the length a of the cavity units, the greater the number of the cavity rows, the better the overall transition effect is, and the number of the cavity rows is properly selected by combining the space structure.
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| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| US20100162679A1 (en) * | 2008-12-31 | 2010-07-01 | Syed Jalaluddin Khalid | Gas turbine engine with ejector |
| US20150047921A1 (en) * | 2013-08-17 | 2015-02-19 | Engineering & Scientific Innovations, Inc. | Fluid flow noise mitigation structure and method |
| CN107701314A (en) * | 2017-11-24 | 2018-02-16 | 厦门大学 | A kind of flow control method that intake duct starting performance is lifted using flexible wall |
| CN109760818A (en) * | 2019-03-21 | 2019-05-17 | 中国人民解放军国防科技大学 | Supersonic velocity boundary layer transition control method based on novel synthetic double-jet actuator |
| CN109779760A (en) * | 2019-01-25 | 2019-05-21 | 中国航天空气动力技术研究院 | Hypersonic inlet turns to twist piece |
| CN112052632A (en) * | 2020-07-27 | 2020-12-08 | 空气动力学国家重点实验室 | Hypersonic flow direction transition prediction method |
| CN112208748A (en) * | 2020-10-13 | 2021-01-12 | 中国人民解放军国防科技大学 | Active and passive combined ultrahigh-speed boundary layer transition broadband control method |
-
2021
- 2021-08-26 CN CN202110986946.XA patent/CN113788151A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| US20100162679A1 (en) * | 2008-12-31 | 2010-07-01 | Syed Jalaluddin Khalid | Gas turbine engine with ejector |
| US20150047921A1 (en) * | 2013-08-17 | 2015-02-19 | Engineering & Scientific Innovations, Inc. | Fluid flow noise mitigation structure and method |
| CN107701314A (en) * | 2017-11-24 | 2018-02-16 | 厦门大学 | A kind of flow control method that intake duct starting performance is lifted using flexible wall |
| CN109779760A (en) * | 2019-01-25 | 2019-05-21 | 中国航天空气动力技术研究院 | Hypersonic inlet turns to twist piece |
| CN109760818A (en) * | 2019-03-21 | 2019-05-17 | 中国人民解放军国防科技大学 | Supersonic velocity boundary layer transition control method based on novel synthetic double-jet actuator |
| CN112052632A (en) * | 2020-07-27 | 2020-12-08 | 空气动力学国家重点实验室 | Hypersonic flow direction transition prediction method |
| CN112208748A (en) * | 2020-10-13 | 2021-01-12 | 中国人民解放军国防科技大学 | Active and passive combined ultrahigh-speed boundary layer transition broadband control method |
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