CN113323756A - Double-flow-passage graded adjustable wide-range air inlet passage, engine and air inlet adjusting method - Google Patents
Double-flow-passage graded adjustable wide-range air inlet passage, engine and air inlet adjusting method Download PDFInfo
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- CN113323756A CN113323756A CN202110692172.XA CN202110692172A CN113323756A CN 113323756 A CN113323756 A CN 113323756A CN 202110692172 A CN202110692172 A CN 202110692172A CN 113323756 A CN113323756 A CN 113323756A
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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
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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
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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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
- F02C7/057—Control or regulation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The invention relates to a ramjet or a combined cycle engine working in a wide range, in particular to a double-runner hierarchical adjustable wide-range air inlet duct, an engine and an air inlet adjusting method, which are used for solving the technical problem that the conventional ramjet and combined cycle engine working in a wide range are difficult to simultaneously consider the performance under high Mach number and the starting capability under low Mach number. This hierarchical adjustable wide range intake duct in double-flow path includes and lies in the intake duct top compression face, intake duct compression face and the curved surface of intake duct throat that the intake duct medial surface lies in proper order along the air current direction to and set up the lip cover at the intake duct lateral surface. Meanwhile, the invention also provides a double-runner grading adjustable wide-range air inlet engine which is a ramjet engine or a combined cycle engine and adopts the double-runner grading adjustable wide-range air inlet. Meanwhile, the invention also provides a double-flow-passage grading adjustable wide-range air inlet adjusting method based on the double-flow-passage grading adjustable wide-range air inlet.
Description
Technical Field
The invention relates to a ramjet engine or a combined cycle engine working in a wide range, in particular to a double-runner hierarchical adjustable wide-range air inlet, an engine and an air inlet adjusting method.
Background
With the revolution and development of engine technology, the demands for ramjet engines and combined cycle engines which work in a wide speed range and high performance are more and more urgent, so that the requirement that an air inlet channel has better performance in a wide Mach number range is required, the conventional fixed geometry air inlet channel is difficult to give consideration to the performance of high and low Mach numbers at present, and the variable geometry air inlet channel can greatly improve the working performance of the air inlet channel by adjusting the contraction ratio of the air inlet channel in the working range, so that the overall performance of the engine is improved. For an air inlet channel working in a wide range, the performance under high Mach and the starting capability under low Mach are mutually restricted, and the performance and the starting capability under low Mach are difficult to simultaneously consider. In order to improve the performance of the air inlet in the flight envelope range, means such as internal compression section air bleeding and air inlet compression amount adjustment are generally adopted, and for Ma2-5 wide-range operating point ramjet engines and combined cycle engines, in order to guarantee the acceleration performance under low Mach number, the flow capturing performance of the air inlet under low Mach number is very important, but the air bleeding scheme reduces the flow capturing performance and increases the resistance, so that the overall technology of the engine is difficult to meet the requirements.
Disclosure of Invention
The invention aims to solve the technical problem that the conventional ramjet engine with a wide-range working point and a combined cycle engine are difficult to simultaneously consider the performance under high Mach number and the starting capability under low Mach number, and provides a double-runner hierarchical adjustable wide-range air inlet, an engine and an air inlet adjusting method.
In order to solve the above problems, the present invention provides the following technical solutions:
the utility model provides a hierarchical adjustable wide region intake duct in double flow way, includes along the air current direction and lies in the intake duct top compression face, intake duct compression face and the curved surface of intake duct throat of intake duct medial surface in proper order to and set up the lip cover at the intake duct lateral surface, its special character lies in:
the device also comprises a flow distribution plate, an adjusting plate and an actuating cylinder;
the flow distribution plate is arranged at the throat part of the air inlet and divides the throat part of the air inlet into two parts, namely an I part and a II part;
the adjusting plate is arranged at the position of the compression surface of the air inlet channel, and the front end of the adjusting plate is arranged on the top compression surface of the air inlet channel through a rotating shaft;
the machine body at the position of the compression surface of the air inlet channel is provided with an installation cavity, the actuating cylinder is positioned in the installation cavity, the movable end of the actuating cylinder extends out of the installation cavity and is hinged with the middle part of the adjusting plate, and the fixed end of the actuating cylinder is hinged with the bottom of the installation cavity;
the adjusting plate, the air inlet top compression surface and the air inlet throat curved surface form a first pneumatic profile, after the actuating cylinder is actuated, the rear end of the adjusting plate is connected with the front end of the flow distribution plate, and the adjusting plate, the air inlet top compression surface and the flow distribution plate form a second pneumatic profile.
Furthermore, the top compression surface of the air inlet channel is a compression surface formed by a wedge shape or a characteristic line and is a front end fixed compression surface on the inner side surface of the air inlet channel.
Furthermore, the top compression surface of the air inlet channel is a compression surface formed by a wedge shape or a characteristic line and is a front end fixed compression surface on the inner side surface of the air inlet channel.
Furthermore, the top compression surface of the air inlet channel adopts a conical and isentropic compression form.
Further, the actuating cylinder is a pneumatic cylinder, a hydraulic cylinder or an electric cylinder.
Further, the initial compression angle of the top compression surface of the air inlet channel is 7.2 degrees, and the total compression angle is 25 degrees.
Further, the length of the throat part of the air inlet channel is 4-6 times of the height of the throat part of the air inlet channel, and an expansion angle of 0.5-2 degrees exists in the throat part of the air inlet channel.
Furthermore, the profile of the lip cover is an arc or a spline curve, and forms an air inlet channel pneumatic flow channel structure with an air inlet channel top compression surface.
Meanwhile, the invention also provides a double-runner hierarchical adjustable wide-range air inlet engine which is a ramjet engine or a combined cycle engine and is characterized in that: the double-flow-passage graded adjustable wide-range air inlet is adopted.
Meanwhile, the invention also provides a double-flow-passage grading adjustable wide-range air inlet adjusting method which is characterized in that based on the double-flow-passage grading adjustable wide-range air inlet, the method comprises the following steps:
(1) calculating to obtain the top compression surface of the air inlet channel by adopting a spiral characteristic line method according to the designed Mach number of the air inlet channel, the initial compression angle and the total compression angle of the top compression surface of the air inlet channel;
(2) determining the ratio of the length of the throat of the air inlet to the height of the throat of the air inlet and the expansion angle of the throat of the air inlet according to the working Mach number range of the air inlet; confirming the position of the splitter plate according to the designed Mach number of the air inlet channel by taking the minimum value of the working Mach number of the air inlet channel as a reference;
(3) when the incoming flow Mach number is lower than the designed Mach number, the adjusting plate is attached to the compression surface of the air inlet channel, and the two parts I and II of the flow channel at the throat part of the air inlet channel are both opened, so that the capture of small compression amount and large flow is realized;
when the incoming flow Mach number is higher than the designed Mach number, the actuator cylinder actuates to enable the adjusting plate to rotate around the rotating shaft, the adjusting plate is connected with the splitter plate, the part II of the flow passage at the throat part of the air inlet channel is open, the part I of the flow passage at the throat part of the air inlet channel is closed, and the total pressure recovery performance of the air inlet channel is improved.
Further, in the step (1), the specific process of calculating the compression surface of the top of the air inlet by using the spiral characteristic curve method is as follows:
determining a parameter after the initial oblique shock wave of the air inlet according to the initial compression angle of 7.2 degrees of the top compression surface 1 of the air inlet, and taking coordinate values (x) of three different points on a characteristic line unit according to the parameter distribution of the top compression surface 11，y1)、(x2，y2)、(x3,y3) The corresponding on the other characteristic line is obtained by adopting the iterative formula of the spiral characteristic line methodDiscrete point coordinate value (x)4,y4) Continuously pushing through the characteristic line grids to generate a top compression surface of the air inlet channel;
the iterative formula of the spiral eigen-curve method is as follows:
wherein: setting a lower angular point of an inlet of the spray pipe as a coordinate origin, wherein x is a horizontal coordinate, the x direction is the horizontal direction of the inlet, y is a vertical coordinate, and the y direction is the normal direction of the horizontal direction; p1～P4Is the static pressure at four points, a is the local acoustic velocity, ρ is the density, V is the velocity, θ is the local flow direction angle, M is the local flow Mach number and M is the local flow Mach number>1, μ is the local flow mach angle, δ is the flow type parameter, δ is 0 for two-dimensional flows and δ is 1 for axisymmetric flows;
is the ordinate y1、y4Average value of (d);
is the ordinate y2、y4Average value of (a).
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the Mach number working range of the air inlet, the double-channel area distribution is carried out on the throat part of the air inlet by arranging the splitter plate, and the requirements of low-Mach-number large-flow capture and high-Mach-number high-total-pressure recovery performance are met.
(2) The adjusting plate, the top compression surface of the air inlet and the curved surface of the throat of the air inlet are positioned on the same pneumatic molded surface, and the adjusting plate is used as a part of the pneumatic molded surface, so that dual control of the flow and the compression quantity of the air inlet is realized.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of a dual-flow staged tunable wide-range inlet of the present invention;
FIG. 2 is a schematic diagram of the embodiment of FIG. 1 operating in the Mach number range of 2-4;
FIG. 3 is a schematic diagram of the embodiment of FIG. 1 operating in the Mach number range of 4-5;
FIG. 4 is a point diagram of total pressure recovery coefficients of a double-runner staged adjustable wide-range air inlet and a fixed geometry air inlet under different Mach numbers.
The reference numbers are as follows: 1-top compression surface of air inlet channel, 11-compression surface of air inlet channel; 2-a rotating shaft; 3, adjusting the plate; 4-an actuator cylinder; 5-lip mask; 6-a splitter plate; 7-inlet throat curved surface; 8-installation cavity.
Detailed Description
The invention will be further described with reference to the drawings and exemplary embodiments.
Referring to fig. 1, the double-runner graded adjustable wide-range air inlet comprises an air inlet top compression surface 1, an air inlet compression surface 11, an air inlet throat curved surface 7, a lip cover 5, a flow distribution plate 6, an adjusting plate 3, an actuating cylinder 4 and an installation cavity 8; the air inlet channel top compression surface 1, the air inlet channel compression surface 11 and the air inlet channel throat curved surface 7 are sequentially located on the inner side surface of the air inlet channel along the air flow direction, the air inlet channel top compression surface 1 is an isentropic curved compression surface generated by a wedge shape or a characteristic line, the air inlet channel top compression surface 1 is an air inlet channel front end fixed compression surface, the expansion direction is unchanged, and the air inlet channel top compression surface is of a binary structure; the molded surface of the lip cover 5 is an arc or spline curve, and forms an air inlet channel pneumatic flow passage structure with the air inlet channel top compression surface 1 to further compress incoming flow; the flow distribution plate 6 is arranged at the throat part of the air inlet and is of a thin-wall structure, and the throat part of the air inlet is divided into two parts, namely an I part and a II part; the adjusting plate 3 is arranged at the position of the compression surface 11 of the air inlet channel, and the front end of the adjusting plate is arranged on the compression surface 1 of the air inlet channel through a rotating shaft 2; be equipped with installation cavity 8 on the organism of intake duct compression face 11 position for isolated air current and thermal-insulated, pressurized strut 4 is located installation cavity 8, and the expansion end of pressurized strut 4 stretches out from installation cavity 8, and articulates with regulating plate 3 middle part, and the stiff end of pressurized strut 4 is articulated with 8 bottoms of installation cavity.
The adjusting plate 3, the air inlet top compression surface 1 and the air inlet throat curved surface 7 form a first pneumatic molded surface, the actuating cylinder 4 enables the adjusting plate 3 to rotate around the rotating shaft 2 in a pneumatic or electric or hydraulic actuating mode, the rear end of the adjusting plate 3 is connected with the front end of the flow distribution plate 6, and the adjusting plate 3, the air inlet top compression surface 1 and the flow distribution plate 6 form a second pneumatic molded surface, so that the shape of a compression surface is adjusted and the flow channel switching is realized.
When the incoming flow mach number is lower than the designed mach number, the adjusting plate 3 is attached to the compression surface 11 of the air inlet channel to form an air inlet channel structure shown in fig. 2, so that the incoming flow capturing capacity of the air inlet channel is improved; when the incoming flow mach number is higher than the design mach number, the actuator cylinder 4 is actuated to enable the adjusting plate 3 to rotate for a certain angle around the rotating shaft 2, so that the adjusting plate 3 is connected with the splitter plate 6 to form the air inlet channel structure shown in figure 3, and the compression capacity of the air inlet channel under the condition of high incoming flow mach number is increased.
In this embodiment, intake duct top compression face 1 adopts awl and isentropic compression form, further improves intake duct compression efficiency and performance, and intake duct design mach number is 4. The initial compression angle of the top compression surface 1 of the air inlet channel is 7.2 degrees, the total compression angle is 25 degrees, the isentropic compression surface is obtained by calculation by a characteristic line method with rotation, and the iterative formula of the characteristic line method with rotation is as follows:
wherein: setting a lower angular point of an inlet of the spray pipe as a coordinate origin, wherein x is a horizontal coordinate, the x direction is the horizontal direction of the inlet, y is a vertical coordinate, and the y direction is the normal direction of the horizontal direction; p1～P4Is the static pressure at four points, a is the local acoustic velocity, ρ is the density, V is the velocity, θ is the local flow direction angle, M is the local flow Mach number and M is the local flow Mach number>1, μ is the local flow mach angle, δ is the flow type parameter, δ is 0 for two-dimensional flows and δ is 1 for axisymmetric flows;
(x1,y1)、(x2,y2)、(x3,y3) Coordinate values of three different points on the known characteristic line unit respectively; (x)4,y4) Is the coordinate value of the corresponding discrete point on the other characteristic line to be solved;
is the ordinate y1、y4Average value of (d);
is the ordinate y2、y4Average value of (a).
In this embodiment, flow distribution plate 6 is located intake duct throat region, intake duct throat length is 4 ~ 6 times of intake duct throat height, there is 0.5 ~ 2 expansion angle in throat, flow distribution plate 6 divide into I and II two parts with the intake duct throat, I and II part proportion are confirmed according to intake duct work mach number scope and design mach number, intake duct work mach number scope is 2 ~ 5, intake duct design mach number is 4, use intake duct throat runner under the mach number 2 state as the benchmark, use design mach number as the basis, be close to organism lateral wall position with the intake duct throat and regard as flow distribution plate 6 position, behind the intake duct throat, I and II two parts runner converge into a runner.
In this embodiment, regulating plate 3 revolutes 2 rotatory regulation compression face shapes of rotation shaft and realizes the runner switching, and at mach number 2 ~ 4 within range, regulating plate 3 and the laminating of intake duct compression face 11, when the incoming flow mach number increases to design mach number 4, regulating plate 3 revolutes 2 rotatory 8 of rotation shaft for regulating plate 3 and flow distribution plate 6 are connected, form the intake duct runner structure that fig. 3 shows.
Referring to fig. 4, through simple variable geometry flow channel adjustment, the total pressure recovery coefficient of the air inlet channel is improved by 60% at mach number 4 and 30.8% at mach number 5 relative to a fixed geometry air inlet channel, and the working performance of the air inlet channel is greatly improved.
According to the scheme of the double-flow-channel graded adjustable wide-range air inlet, the throat flow channel of the air inlet is reasonably designed, the flow channel of the throat of the air inlet is divided into two parts through the flow dividing support plate, and the small compression amount and the large flow capture are realized by completely opening the throat flow channel in the low-Mach working range; in a high Mach number working range, one of the runners is closed, so that the compression amount of the air inlet channel is increased, and the total pressure recovery performance of the air inlet channel is improved.
The invention also provides a double-flow-passage grading adjustable wide-range air inlet adjusting method, which adopts the double-flow-passage grading adjustable wide-range air inlet and comprises the following steps:
(1) determining a parameter after the initial oblique shock wave of the air inlet according to the initial compression angle of 7.2 degrees of the top compression surface 1 of the air inlet, and taking coordinate values (x) of three different points on a characteristic line unit according to the parameter distribution of the top compression surface 1 of the air inlet1,y1)、(x2,y2)、(x3，y3) Calculating by using an iterative formula of a spiral characteristic line method to obtain the coordinate value (x) of a corresponding discrete point on the other characteristic line4,y4) Continuously pushing through the characteristic line grids to generate a top compression surface of the air inlet channel;
the iterative formula of the spiral eigen-curve method is:
wherein: setting a lower angular point of an inlet of the spray pipe as a coordinate origin, wherein x is a horizontal coordinate, the x direction is the horizontal direction of the inlet, y is a vertical coordinate, and the y direction is the normal direction of the horizontal direction; p is the local static pressure, a is the local acoustic velocity, θ is the local flow direction angle, M is the local flow mach number and M >1, μ is the local flow mach angle, δ is the flow type parameter, δ is 0 for two-dimensional flows and δ is 1 for axisymmetric flows;
(2) determining that the length of the throat of the air inlet is 4-6 times of the height of the throat of the air inlet according to the working Mach number range of the air inlet being 2-5, and the throat has an expansion angle of 0.5-2 degrees; then, the minimum value 2 of the working Mach number of the air inlet channel is taken as a reference, the Mach number 4 is designed according to the air inlet channel, and the position of the throat part of the air inlet channel, which is close to one side wall surface of the machine body, is taken as the position of a splitter plate 6;
(3) when the incoming flow Mach number is lower than the designed Mach number, the adjusting plate 3 is attached to the compression surface 11 of the air inlet channel, and the two parts I and II of the flow channel at the throat part of the air inlet channel are both opened, so that the capture of small compression amount and large flow amount is realized;
when the incoming flow Mach number is higher than the designed Mach number, the actuator cylinder 4 actuates to enable the adjusting plate 3 to rotate 8 degrees around the rotating shaft 2, the adjusting plate 3 is connected with the splitter plate 6, the part II of the flow passage at the throat part of the air inlet channel is open, the part I of the flow passage at the throat part of the air inlet channel is closed, and the total pressure recovery performance of the air inlet channel is improved.
The above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, and it is obvious for a person skilled in the art to modify the specific technical solutions described in the foregoing embodiments or to substitute part of the technical features, and these modifications or substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions protected by the present invention.
Claims (10)
1. The utility model provides a hierarchical adjustable wide region intake duct of double-flow-passage, includes along airflow direction and lies in intake duct top compression face (1), intake duct compression face (11) and intake duct throat curved surface (7) of intake duct medial surface in proper order to and set up lip cover (5) at the intake duct lateral surface, its characterized in that:
the device also comprises a flow distribution plate (6), an adjusting plate (3) and an actuating cylinder (4);
the flow distribution plate (6) is arranged at the throat part of the air inlet, and two sides of the flow distribution plate are connected with the wall surface of the throat part of the air inlet to divide the throat part of the air inlet into an I part and a II part;
the adjusting plate (3) is arranged at the position of the air inlet compression surface (11), and the front end of the adjusting plate is arranged on the air inlet top compression surface (1) through a rotating shaft (2);
an installation cavity (8) is formed in the engine body at the position of the air inlet compression surface (11), the actuating cylinder (4) is located in the installation cavity (8), the movable end of the actuating cylinder (4) extends out of the installation cavity (8) and is hinged to the middle of the adjusting plate (3), and the fixed end of the actuating cylinder (4) is hinged to the bottom of the installation cavity (8);
adjusting plate (3) and intake duct top compression face (1) and intake duct throat curved surface (7) form first pneumatic profile, actuator cylinder (4) actuate the back, and the rear end of adjusting plate (3) is connected with the front end of flow distribution plate (6), and adjusting plate (3) and intake duct top compression face (1) and flow distribution plate (6) form the pneumatic profile of second.
2. The dual-runner staged adjustable wide range air inlet duct of claim 1, wherein: the air inlet top compression surface (1) is a compression surface formed by a wedge shape or a characteristic line and is a compression surface fixed at the front end of the inner side surface of the air inlet.
3. The dual-runner staged adjustable wide range air inlet duct of claim 2, wherein: the top compression surface (1) of the air inlet channel adopts a conical and isentropic compression form.
4. The dual-runner staged adjustable wide range air inlet duct of claim 3, wherein: the actuating cylinder (4) is a pneumatic cylinder, a hydraulic cylinder or an electric cylinder.
5. The dual-runner staged adjustable wide range air inlet duct of claim 4, wherein: the initial compression angle of the top compression surface (1) of the air inlet channel is 7.2 degrees, and the total compression angle is 25 degrees.
6. The dual-runner staged adjustable wide range air inlet duct of claim 5, wherein: the length of the throat part of the air inlet channel is 4-6 times of the height of the throat part of the air inlet channel, and the throat part of the air inlet channel has an expansion angle of 0.5-2 degrees.
7. The dual-runner staged adjustable wide range air inlet duct of claim 6, wherein: the molded surface of the lip cover (5) is an arc or a spline curve, and forms an air inlet channel pneumatic flow passage structure with the air inlet channel top compression surface (1).
8. The utility model provides a hierarchical adjustable wide region intake duct engine of double-flow passage, is ramjet or combined cycle engine which characterized in that: the use of a dual-channel staged widenable inlet according to any of claims 1 to 7.
9. A double-runner classification adjustable wide-range air inlet adjusting method is characterized in that the double-runner classification adjustable wide-range air inlet based on claim 1 comprises the following steps:
(1) calculating to obtain the top compression surface (1) of the air inlet channel by adopting a spiral characteristic line method according to the designed Mach number of the air inlet channel, the initial compression angle and the total compression angle of the top compression surface (1) of the air inlet channel;
(2) determining the ratio of the length of the throat of the air inlet to the height of the throat of the air inlet and the expansion angle of the throat of the air inlet according to the working Mach number range of the air inlet; confirming the position of the splitter plate (6) according to the designed Mach number of the air inlet channel by taking the minimum value of the working Mach number of the air inlet channel as a reference;
(3) when the incoming flow Mach number is lower than the designed Mach number, the adjusting plate (3) is attached to the compression surface (11) of the air inlet channel, and the two parts I and II of the flow channel at the throat part of the air inlet channel are both opened, so that the capture of small compression amount and large flow amount is realized;
when the incoming flow Mach number is higher than the designed Mach number, the actuator cylinder (4) is actuated to enable the adjusting plate (3) to rotate around the rotating shaft (2), the adjusting plate (3) is connected with the splitter plate (6), the part II of the flow passage at the throat part of the air inlet channel is open, the part I of the flow passage at the throat part of the air inlet channel is closed, and the total pressure recovery performance of the air inlet channel is improved.
10. The dual-runner staged adjustable wide-range air intake conditioning method of claim 9, wherein: in the step (1), the specific process of calculating the top compression surface (1) of the air inlet channel by adopting the spiral characteristic line method is as follows:
determining a parameter after the initial oblique shock wave of the air inlet according to the initial compression angle of the top compression surface (1) of the air inlet, and taking coordinate values (x) of three different points on a characteristic line unit according to the parameter distribution of the top compression surface (1) of the air inlet1,y1)、(x2,y2)、(x3,y3) Calculating by using an iterative formula of a spiral characteristic line method to obtain the coordinate value (x) of a corresponding discrete point on the other characteristic line4,y4) Continuously pushing through the characteristic line grids to generate an air inlet top compression surface (1);
the iterative formula of the spiral eigen-curve method is as follows:
wherein: setting the lower angular point of the nozzle inlet as the coordinateThe original point, x is the abscissa, the x direction is the horizontal direction of the inlet, y is the ordinate, the y direction is the normal direction of the horizontal direction; p1～P4Is the static pressure at four points, a is the local acoustic velocity, ρ is the density, V is the velocity, θ is the local flow direction angle, M is the local flow Mach number and M is the local flow Mach number>1, μ is the local flow mach angle, δ is the flow type parameter, δ is 0 for two-dimensional flows and δ is 1 for axisymmetric flows;
is the ordinate y1、y4Average value of (d);
is the ordinate y2、y4Average value of (a).
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| CN114151826A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Variable geometry combustion chamber |
Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB896982A (en) * | 1958-07-18 | 1962-05-23 | Bristol Siddeley Engines Ltd | Improvements in jet propulsion power plants for aircraft |
| US3937238A (en) * | 1975-02-25 | 1976-02-10 | United Technologies Corporation | Variable area engine inlet |
| WO1999033701A2 (en) * | 1997-12-29 | 1999-07-08 | Vladimir Timofeevich Medvedev | Self-adjusting air intake |
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| JP2009041418A (en) * | 2007-08-08 | 2009-02-26 | Japan Aerospace Exploration Agency | Air-breathing engine for space transport and method of improving its accelerating performance |
| CN102278232A (en) * | 2011-05-26 | 2011-12-14 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN102518517A (en) * | 2011-12-08 | 2012-06-27 | 南京航空航天大学 | Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet |
| CN106342120B (en) * | 2009-01-05 | 2013-07-24 | 中国空空导弹研究院 | Integrated ducted rocket inlet mouth boosting/punching press conversion equipment |
| EP2708272A1 (en) * | 2012-09-17 | 2014-03-19 | Honeywell International Inc. | Inlet particle separator systems |
| CN103678774A (en) * | 2013-11-15 | 2014-03-26 | 南京航空航天大学 | Designing method for supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness |
| US20150122954A1 (en) * | 2013-11-07 | 2015-05-07 | Sikorsky Aircraft Corporation | Variable geometry helicopter engine inlet |
| CN104727944A (en) * | 2015-01-19 | 2015-06-24 | 西安航天动力研究所 | Structure of rocket-based-combined power engine capable of broadening working range of fixed-geometry air inlet channel |
| CN105156228A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Ejector-assistant turbine-based combined cycle engine |
| CN106150757A (en) * | 2016-08-10 | 2016-11-23 | 西北工业大学 | A kind of dual pathways becomes geometry rocket based combined cycle electromotor |
| CN106285946A (en) * | 2016-08-01 | 2017-01-04 | 南京航空航天大学 | The passage of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle |
| CN107023395A (en) * | 2017-06-07 | 2017-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | The supersonic aircraft air intake duct and adjusting method of a kind of adjustable throat area |
| CN107061011A (en) * | 2017-06-02 | 2017-08-18 | 南京航空航天大学 | Low extrernal resistance hypersonic inlet |
| CN107091157A (en) * | 2017-06-05 | 2017-08-25 | 南京航空航天大学 | A kind of imperial palace shrinkage ratio, determine geometry binary hypersonic inlet and design method |
| CN107575309A (en) * | 2017-08-07 | 2018-01-12 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake ducts and design method |
| CN211287901U (en) * | 2019-10-11 | 2020-08-18 | 南京航空航天大学 | Ma0-6+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet |
| CN111553976A (en) * | 2020-04-27 | 2020-08-18 | 南昌航空大学 | Design method of three-dimensional inward-rotation air inlet channel with shock wave and pressure distribution controllable simultaneously |
| CN212272395U (en) * | 2020-05-27 | 2021-01-01 | 厦门大学 | Improve splitter plate of TBCC intake duct modal transformation gas tightness |
-
2021
- 2021-06-22 CN CN202110692172.XA patent/CN113323756B/en active Active
Patent Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB896982A (en) * | 1958-07-18 | 1962-05-23 | Bristol Siddeley Engines Ltd | Improvements in jet propulsion power plants for aircraft |
| US3937238A (en) * | 1975-02-25 | 1976-02-10 | United Technologies Corporation | Variable area engine inlet |
| WO1999033701A2 (en) * | 1997-12-29 | 1999-07-08 | Vladimir Timofeevich Medvedev | Self-adjusting air intake |
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| JP2009041418A (en) * | 2007-08-08 | 2009-02-26 | Japan Aerospace Exploration Agency | Air-breathing engine for space transport and method of improving its accelerating performance |
| CN106342120B (en) * | 2009-01-05 | 2013-07-24 | 中国空空导弹研究院 | Integrated ducted rocket inlet mouth boosting/punching press conversion equipment |
| CN102278232A (en) * | 2011-05-26 | 2011-12-14 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN102518517A (en) * | 2011-12-08 | 2012-06-27 | 南京航空航天大学 | Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet |
| EP2708272A1 (en) * | 2012-09-17 | 2014-03-19 | Honeywell International Inc. | Inlet particle separator systems |
| US20150122954A1 (en) * | 2013-11-07 | 2015-05-07 | Sikorsky Aircraft Corporation | Variable geometry helicopter engine inlet |
| CN103678774A (en) * | 2013-11-15 | 2014-03-26 | 南京航空航天大学 | Designing method for supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness |
| CN104727944A (en) * | 2015-01-19 | 2015-06-24 | 西安航天动力研究所 | Structure of rocket-based-combined power engine capable of broadening working range of fixed-geometry air inlet channel |
| CN105156228A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Ejector-assistant turbine-based combined cycle engine |
| CN106285946A (en) * | 2016-08-01 | 2017-01-04 | 南京航空航天大学 | The passage of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle |
| CN106150757A (en) * | 2016-08-10 | 2016-11-23 | 西北工业大学 | A kind of dual pathways becomes geometry rocket based combined cycle electromotor |
| CN107061011A (en) * | 2017-06-02 | 2017-08-18 | 南京航空航天大学 | Low extrernal resistance hypersonic inlet |
| CN107091157A (en) * | 2017-06-05 | 2017-08-25 | 南京航空航天大学 | A kind of imperial palace shrinkage ratio, determine geometry binary hypersonic inlet and design method |
| CN107023395A (en) * | 2017-06-07 | 2017-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | The supersonic aircraft air intake duct and adjusting method of a kind of adjustable throat area |
| CN107575309A (en) * | 2017-08-07 | 2018-01-12 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake ducts and design method |
| CN211287901U (en) * | 2019-10-11 | 2020-08-18 | 南京航空航天大学 | Ma0-6+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet |
| CN111553976A (en) * | 2020-04-27 | 2020-08-18 | 南昌航空大学 | Design method of three-dimensional inward-rotation air inlet channel with shock wave and pressure distribution controllable simultaneously |
| CN212272395U (en) * | 2020-05-27 | 2021-01-01 | 厦门大学 | Improve splitter plate of TBCC intake duct modal transformation gas tightness |
Non-Patent Citations (5)
| Title |
|---|
| JUN LIU等: "Experimental and numerical investigation of smooth turbine-based", 《AEROSPACE SCIENCE AND TECHNOLOGY》 * |
| 倪凯捷: "TBCC可调二元进气道设计方法研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
| 李文龙等: "局部进气条件下空气涡轮火箭发动机掺混燃烧研究", 《推进技术》 * |
| 艾军军: "分区双模超燃冲压燃烧组织方案研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
| 谭慧俊等: "基于激波形状控制的定几何高超声速可调进气道概念及初步验证", 《中国科学(E辑:技术科学)》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151826A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Variable geometry combustion chamber |
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