CN110450964B - Axisymmetric inclined outlet convergent-divergent nozzle and design method thereof - Google Patents
Axisymmetric inclined outlet convergent-divergent nozzle and design method thereof Download PDFInfo
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- CN110450964B CN110450964B CN201810427675.2A CN201810427675A CN110450964B CN 110450964 B CN110450964 B CN 110450964B CN 201810427675 A CN201810427675 A CN 201810427675A CN 110450964 B CN110450964 B CN 110450964B
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000007921 spray Substances 0.000 claims abstract description 18
- 238000002679 ablation Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 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
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a quasi-axisymmetric inclined outlet convergent-divergent nozzle and a design method thereof, belongs to the field of aircrafts, and aims to provide a quasi-axisymmetric inclined outlet convergent-divergent nozzle and a design method thereof, wherein the technical scheme is as follows: 1) the jet pipe comprises a jet pipe through which air flows by the flow characteristics of an axisymmetric jet pipe, wherein an air outlet of the jet pipe is obliquely arranged; 2) the design steps are as follows: calculating to obtain an initial flow field based on a characteristic line method, and obtaining the molded surface of the original axisymmetric spray pipe; in the plane of the original nozzle throat section, making the throat section circle (target circle for short) of the target nozzle tangent with the inside of the throat section circle, and establishing the corresponding relation between the target circle and the original nozzle throat section; and carrying out streamline tracing in the initial flow field according to the target circle, and obtaining the molded surface of the spray pipe through three-dimensional modeling design. The invention has the advantages that: 1. the maximum thrust characteristic of the axisymmetric nozzle is provided; 2. the inclined outlet of the spray pipe can avoid the occurrence of the phenomenon of wiping the ground at the tail of the machine; 3. the weight is reduced; 4. protecting the body from high temperature ablation.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to an axisymmetric inclined outlet convergent-divergent nozzle and a design method thereof.
Background
In the design of the tail nozzle of the aeroengine, the axisymmetric nozzle designed based on the characteristic line method has the advantages of high thrust coefficient and uniform outlet airflow, and is widely applied to the aeroengine field. However, if the full-flow state is to be achieved, the length of the axisymmetric nozzle designed by the characteristic line method is longer, the weight of the airplane is increased, and the tail wiping situation is more likely to occur for the horizontal take-off and landing aircraft. The commonly used solution is to directly truncate the axisymmetric nozzle designed by the characteristic line method, but the thrust coefficient is bound to be reduced, and the situation that the high-temperature gas exhausted by an engine ablates the surface of the aircraft body can also occur in the flying process of the aircraft.
Disclosure of Invention
The invention aims to provide an axisymmetric inclined outlet convergent-divergent nozzle which has the advantages that: under the condition of having the maximum thrust characteristic of the axisymmetric nozzle, the phenomenon of wiping the ground at the tail of the machine can be avoided, and the problem of structural layout is solved; meanwhile, the spray pipe is an inclined outlet, so that a longer wall surface of the spray pipe is reserved on one side close to the machine body, and a shorter wall surface is reserved on one side far away from the machine body, so that the machine body is protected from high-temperature ablation, and the weight is reduced.
The technical purpose of the invention is realized by the following technical scheme: the jet pipe comprises a jet pipe body, wherein the jet pipe body comprises an air inlet and an air outlet, a throat is arranged between the air inlet and the air outlet, the air outlet of the jet pipe body is obliquely arranged, and the air flow in the jet pipe body has the flow characteristic of an axisymmetric jet pipe.
Through the scheme, the target nozzle has the flow characteristic of the axisymmetric nozzle due to the fact that the air flow in the nozzle has the flow characteristic of the axisymmetric nozzle, and the air flow is fully expanded in the nozzle, so that the thrust characteristic of the target nozzle is the same as that of the axisymmetric nozzle, namely the thrust coefficient is the maximum. Meanwhile, as the spray pipe is an inclined outlet, a longer wall surface is reserved on one side of the spray pipe close to the machine body, and a shorter wall surface is reserved on one side far away from the machine body. Therefore, the target nozzle can protect the machine body from high-temperature ablation under the condition of having the maximum thrust characteristic of the axisymmetric nozzle, reduce the weight of the machine body, avoid the phenomenon of wiping the ground at the tail of the machine and solve the problem of structural layout.
Another object of the present invention is to provide a design method for designing the above-mentioned axisymmetric inclined outlet convergent-divergent nozzle, comprising the following steps:
calculating an initial flow field based on a characteristic line method, and obtaining an original axisymmetric spray pipe through the spray pipe wall surface calculated by the characteristic line;
taking a throat section on the original axisymmetric nozzle as an initial section, and establishing an XOY rectangular coordinate system by taking a circle center O of the initial section as an origin;
selecting a target circle positioned in the initial section in the XOY rectangular coordinate system, and setting the target circle as the throat section of the target pipe body;
taking a series of discrete points P on a target circle, and determining a target point corresponding to the point P on the initial section of the original axisymmetric nozzle;
in the initial flow field, respectively making streamlines which pass through the target points according to a streamline tracing method;
and taking the streamline as curve segments, and making a curved surface passing through the curve segments to obtain the wall surface of the target spray pipe.
Through the scheme, the model of the target spray pipe can be rapidly and conveniently generated.
Furthermore, any point O 'is taken in the initial section, and a circle inscribed with the initial section is taken as a target circle by taking the O' as a center of the circle.
By the scheme, an operator can quickly obtain a target circle in the initial section.
Further, the coordinate of the point P on any target circle under the XOY rectangular coordinate system is determined, the line segment OP is rotated to the Y coordinate axis around the coordinate origin O, and the obtained point P' is the target point of the point P corresponding to the original nozzle throat radius.
By the scheme, an operator can quickly and conveniently obtain the corresponding target points of any point on the target circle on the original nozzle throat radius, and make the flow line passing through the target points in the initial characteristic line flow field.
Furthermore, an included angle beta between the line segment OP and the Y axis is taken, the included angle beta is taken as a rotation angle, a series of curve segments are respectively rotated by an angle beta around the axis of the original axisymmetric nozzle, and the wall surface of the target nozzle is obtained through three-dimensional modeling.
Through the scheme, a series of curved surfaces can be obtained by respectively rotating a series of curved sections by beta angles around the axis of the original axisymmetric nozzle, and the surfaces in the intersection lines of all the curved surfaces are integrated through three-dimensional modeling, so that the wall surface of the target nozzle can be quickly and conveniently obtained.
In conclusion, the invention has the following beneficial effects:
1. under the condition of not losing thrust, the contradiction between the thrust of the spray pipe and the length of the spray pipe is solved, the possibility of wiping the ground at the tail of the airplane is reduced, and the safety of the airplane during taking off and landing is improved;
2. the spray pipe is an inclined outlet, so that a longer wall surface of the spray pipe is reserved on one side close to the engine body, and a shorter wall surface of the spray pipe is arranged on one side far away from the engine body.
Drawings
FIG. 1 is a schematic structural diagram of an original axisymmetric nozzle embodying the present embodiment;
FIG. 2 is a schematic diagram of the present embodiment for embodying the throat design;
fig. 3 is a schematic structural diagram of the target tube according to the embodiment.
In the figure, 1, a spray pipe; 11. an air inlet; 12. an air outlet; 2. a throat; 3. an original axisymmetric nozzle; 31. an initial cross-section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
In which like parts are designated by like reference numerals. It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "bottom" and "top," "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.
Referring to fig. 1, an initial flow field is calculated based on a characteristic line method, and an original axisymmetric nozzle 3 is generated from the nozzle wall surface calculated by the characteristic line.
Referring to fig. 1 and 2, the throat cross section of the original axisymmetric nozzle 3 is set to be an initial cross section 31, and the radius of the initial cross section 31 is set to be 50 mm. Establishing an XOY rectangular coordinate system by taking the circle center O of the initial section 31 as a zero point;
an arbitrary point O 'is taken within the initial cross-section 31, where the coordinates of the point O' are taken to be (0, 20 mm). And taking O' as the center of a circle to make a target circle internally tangent with the initial section 31, wherein the coordinate formula of the target circle is as follows: x is the number of2+（y-20）2= 900. Setting the target circle as the section of the throat 2 of the target nozzle 1;
a series of discrete points P are taken on the circle, where one of the points P is chosen to have an abscissa of 18 mm. According to the coordinate formula of the target circle, the vertical coordinate of the point P in the XOY rectangular coordinate system is 44mm, and accordingly, the corresponding coordinate of the point P on the initial section 31 of the original axisymmetric nozzle 3 is (18 mm, 44 mm).
Rotating the line segment OP to the Y coordinate axis around the coordinate origin O to obtain a P' point which is a target point of the P point corresponding to the original nozzle throat radius, and respectively making streamlines passing through the target points in the initial characteristic line flow field according to a streamline tracing method;
at this time, an included angle between the line segment OP and the Y axis is set as beta, the streamline is set as a curve segment, an angle of the included angle beta is set as a rotation angle, and the series of curves are respectively rotated by the angle beta.
As shown in fig. 3, a series of curved sections are respectively rotated by an angle β around the axis of the original axisymmetric nozzle to obtain a series of curved surfaces, and the series of curved surfaces are three-dimensionally shaped to integrate the surfaces in the intersecting lines of all the curved surfaces, thereby quickly and conveniently obtaining the wall surface of the target nozzle 1.
As shown in FIG. 3, when the gas flow flows from the air inlet 11 and the throat 2 of the nozzle 1 to the air outlet 12, the flow of the gas flow in the nozzle has the flow characteristic of the axisymmetric nozzle, so that the thrust characteristic of the target nozzle is the same as that of the axisymmetric nozzle, the gas is completely expanded, namely the maximum thrust coefficient is obtained, meanwhile, the tail rubbing of the airplane can be avoided, and the safety of the airplane during taking off and landing is improved.
As shown in fig. 3, the nozzle 1 is an inclined outlet, which can ensure that the nozzle 1 has a longer wall surface at the side close to the machine body and a shorter wall surface at the side far from the machine body, and compared with an axisymmetric nozzle, the nozzle can protect the machine body from high-temperature ablation and reduce the weight of the machine body.
The above embodiment focuses on the generation process of the nozzle 1 with the circular throat 2, and the sectional shape of the throat 2 of the target nozzle 1 may also be a quasi-circular shape or any other closed curve to generate nozzles with various shapes as required, and the generation principle of the target nozzle 1 is the same as the above principle.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications of the present embodiment without inventive contribution as needed after reading the present specification, but all of them are protected by patent law within the scope of the claims of the present invention.
Claims (4)
1. A design method of a similar axisymmetric inclined outlet convergent-divergent nozzle is characterized by comprising the following steps: the jet pipe comprises a jet pipe (1), wherein the jet pipe (1) comprises an air inlet (11) and an air outlet (12), a throat (2) is arranged between the air inlet (11) and the air outlet (12), the air outlet (12) of the jet pipe (1) is obliquely arranged, and the flow of air flow in the jet pipe (1) has the flow characteristic of an axisymmetric jet pipe;
the method comprises the following steps:
calculating an initial flow field based on a characteristic line method, and obtaining an original axisymmetric nozzle (3) through the wall surface of the nozzle calculated by the characteristic line;
taking a throat section on the original axisymmetric nozzle (3) as an initial section (31), and establishing an XOY rectangular coordinate system by taking a circle center O of the initial section (31) as an origin;
selecting a target circle positioned in the initial section (31) in the XOY rectangular coordinate system, and setting the target circle as the section of the throat (2) of the target nozzle (1);
taking a series of discrete points P on a target circle, and determining a target point corresponding to the point P on an initial section (31) of the original axisymmetric nozzle (3);
in the initial flow field, respectively making streamlines which pass through the target points according to a streamline tracing method;
and taking the streamline as curve segments, and making a curved surface passing through the curve segments to obtain the wall surface of the target spray pipe (1).
2. The method of claim 1 wherein the design of the axisymmetric oblique exit convergent-divergent nozzle is as follows: and taking any point O 'in the initial section (31), and taking a circle inscribed with the initial section (31) as a target circle by taking the O' as a center of the circle.
3. The method of claim 1 wherein the design of the axisymmetric oblique exit convergent-divergent nozzle is as follows: and determining the coordinate of the point P on any target circle under an XOY rectangular coordinate system, and rotating the line segment OP to the Y coordinate axis around the coordinate origin O to obtain a point P', namely a target point corresponding to the point P on the original nozzle throat radius.
4. The method of claim 3 wherein the design of the axisymmetric oblique exit convergent-divergent nozzle is as follows: and taking an included angle beta between the line segment OP and the Y axis, taking the included angle beta as a rotation angle, respectively rotating a series of curve segments by an angle beta around the axis of the original axisymmetric nozzle, and obtaining the wall surface of the target nozzle (1) through three-dimensional modeling.
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| CN201810427675.2A CN110450964B (en) | 2018-05-07 | 2018-05-07 | Axisymmetric inclined outlet convergent-divergent nozzle and design method thereof |
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| CN201810427675.2A CN110450964B (en) | 2018-05-07 | 2018-05-07 | Axisymmetric inclined outlet convergent-divergent nozzle and design method thereof |
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| CN110450964B true CN110450964B (en) | 2020-11-24 |
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2018
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| US2657575A (en) * | 1947-08-21 | 1953-11-03 | Harry J Allen | Asymmetric adjustable supersonic nozzle |
| US3080711A (en) * | 1960-01-06 | 1963-03-12 | James F Connors | Penshape exhaust nozzle for supersonic engine |
| DE1175036B (en) * | 1960-07-01 | 1964-07-30 | Rolls Royce | Aircraft jet engine plant |
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| CN110450964A (en) | 2019-11-15 |
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