CN114046211A - Combined power adjustable spray pipe with double expansion sections - Google Patents
Combined power adjustable spray pipe with double expansion sections Download PDFInfo
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- CN114046211A CN114046211A CN202111319546.XA CN202111319546A CN114046211A CN 114046211 A CN114046211 A CN 114046211A CN 202111319546 A CN202111319546 A CN 202111319546A CN 114046211 A CN114046211 A CN 114046211A
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- 239000007921 spray Substances 0.000 title abstract description 44
- 230000002093 peripheral effect Effects 0.000 claims abstract description 4
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 230000009977 dual effect Effects 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 description 7
- 239000002737 fuel gas Substances 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000000926 separation method Methods 0.000 description 5
- 238000006049 ring expansion reaction Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention discloses a combined power adjustable spray pipe with double expansion sections, which is arranged on an aircraft engine and comprises an outer ring spray pipe and a main spray pipe, wherein the outer ring spray pipe is positioned on the outer peripheral side of the main spray pipe; the outer ring spray pipe sequentially comprises a connecting section, a first expansion section and a second expansion section from one end to the other end, and an inflection point is arranged at the joint of the first expansion section and the second expansion section; the main nozzle comprises a main nozzle convergence section and a main nozzle expansion section, a main nozzle throat is arranged at the inner side intersection between the main nozzle convergence section and the main nozzle expansion section, an outer ring nozzle throat is formed at the joint of the connecting section and the first expansion section and the outer wall surface of the main nozzle expansion section, and the area of the outer ring nozzle throat is adjusted by the connecting section and the first expansion section in a corresponding axial movement mode.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a combined power adjustable spray pipe with double expansion sections.
Background
Aiming at the working requirements of a hypersonic aircraft, a tail nozzle of the hypersonic aircraft needs to work in an extremely wide range of pressure drop ratio, and meanwhile, in order to meet the thrust performance of the aircraft in low altitude and high altitude flight, a precooling rocket combined power device is an attractive scheme.
For a conventionally designed dual-mode combined power plant, the air-breathing mode and rocket mode nozzle exit flow areas remain constant in both the air-breathing mode operating with outer annular nozzle bleed and the rocket mode operating with central nozzle bleed, which is highly susceptible to severe thrust losses for nozzles that are required to undergo a take-off from ground to high altitude approach. If the exhaust system is designed by taking the high altitude state as a design point, the gas is easy to have serious over expansion under the ground takeoff state, and the unstable separation is generated on the inner side boundary surface to cause strong lateral load, thereby influencing the working performance and the flight safety of the aircraft. And if the exhaust system is designed by taking a low altitude state or a transition state as a design point, higher under-expansion loss is generated in the high altitude state, and the thrust efficiency of the spray pipe is influenced. Meanwhile, considering the influence of the flow coefficient of the air inlet channel in the air suction mode and the unstable combustion factor of the combustion chamber, the throat area of the spray pipe needs to be freely adjusted to adapt to the engine state and realize flow adjustment.
Therefore, how to provide a combined power variable nozzle with double expansion sections, which can freely adjust the throat area to adapt to the engine state, is a problem to be solved by those skilled in the art.
Disclosure of Invention
In view of the above, the present invention provides a combined power adjustable nozzle with two expansion sections, which is convenient for adjusting the throat area to adapt to the flow state of the engine and improve the thrust efficiency of the nozzle.
In order to achieve the purpose, the invention adopts the following technical scheme: a combined power adjustable spray pipe with double expansion sections is installed on an aircraft engine and comprises an outer ring spray pipe and a main spray pipe, wherein the outer ring spray pipe is positioned on the outer peripheral side of the main spray pipe, the outer ring spray pipe is connected to an engine body in a sliding mode through an actuating adjusting system at a tail spray opening of the aerospace engine, a hydraulic cylinder and a servo mechanism of the actuating adjusting system adjust axial movement of the outer ring spray pipe, and the main spray pipe is communicated with a thrust chamber of the engine; the outer ring spray pipe sequentially comprises a connecting section, a first expansion section and a second expansion section from one end to the other end, and an inflection point is arranged at the joint of the first expansion section and the second expansion section; the main nozzle comprises a main nozzle convergence section and a main nozzle expansion section, the inner side intersection between the main nozzle convergence section and the main nozzle expansion section is a main nozzle throat, an outer ring nozzle throat is formed on the outer wall surface of the main nozzle expansion section and the connection intersection between the connection section and the first expansion section, and the connection section and the first expansion section move axially correspondingly to adjust the sectional area of the outer ring nozzle throat.
The invention has the beneficial effects that: the gas expansion joint has an inflection point when the first expansion section is connected with the second expansion section, and the gas is stably separated at the inflection point under the condition of low pressure drop ratio, so that the over-expansion phenomenon caused by the continuous expansion of the gas in the second expansion section is avoided. The over expansion refers to a state that air flow expands in the spray pipe until static pressure on an outlet section is smaller than external atmospheric pressure, strong shock waves are generated in a pipe opening or a pipe, and finally thrust loss is serious, so that thrust loss of the spray pipe is caused.
Preferably, the diameter of the outer circumference of the main nozzle is gradually increased corresponding to the direction from the convergent section of the main nozzle to the divergent section of the main nozzle.
Preferably, the inner diameter of the large-caliber end corresponding to the first expansion section is equal to the inner diameter of the small-caliber end corresponding to the second expansion section.
Preferably, the main nozzle expansion section is in a horn shape, and the outer wall surface of the main nozzle expansion section sequentially comprises an arc section and a straight line section corresponding to the central axial direction of the main nozzle expansion section; the arc-shaped half diameter of the arc-shaped section is larger than that of the first expansion section; the large-caliber end of the first expansion section and the large-caliber end of the main nozzle expansion section are in the same direction.
Preferably, the diameter size of the main nozzle expanding section corresponding to the large-caliber end is larger than the inner diameter size of the connecting section.
Preferably, the included angle between the straight line section corresponding to the outer wall surface of the main nozzle expansion section and the central axis is 5-20 degrees.
Preferably, the profile arcs of the first expansion section and the second expansion section are determined by second-order parabolas, and an included angle between an outlet tangent of the first expansion section corresponding to the air injection direction and a horizontal line is 0-45 degrees; the second expansion section is corresponding to the export tangent line of gas-jet direction and is 0 ~ 15 with the horizontal line contained angle.
Drawings
FIG. 1 is a first schematic view of a combined power variable nozzle with dual diverging sections according to the present invention;
FIG. 2 is a schematic view of a second embodiment of a combined power variable nozzle with dual diverging sections according to the present invention;
FIG. 3 is a schematic structural view of a combined power variable nozzle with a double expansion section according to the present invention;
FIG. 4 is a graph comparing the flow characteristics of a combination dynamically variable nozzle with dual diverging sections of the present invention with a bell nozzle design having the same exit area.
The main nozzle comprises an outer ring nozzle 1, a connecting section 11, a first expanding section 12, a second expanding section 13, a main nozzle 2, a main nozzle converging section 21, a main nozzle expanding section 22, an arc section 221, a straight section 222, a 3-action adjusting system, a main nozzle throat 4, an outer ring nozzle throat 5, a main nozzle outlet 6 and an outer ring nozzle outlet 7.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to the attached drawings 1 to 4 of the invention, the combined power adjustable nozzle with the double expansion sections according to the embodiment of the invention is installed on an aircraft engine and comprises an outer ring nozzle 1 and a main nozzle 2, wherein the outer ring nozzle 1 is positioned on the outer peripheral side of the main nozzle 2, the outer ring nozzle 1 is connected to an engine body in a sliding mode through an actuating adjusting system 3 at a tail nozzle of the aerospace engine, a hydraulic actuating cylinder and a servo mechanism of the actuating adjusting system adjust the axial movement of the outer ring nozzle 1, and the main nozzle 2 is communicated with a thrust chamber of the engine; the outer ring nozzle 1 sequentially comprises a connecting section 11, a first expansion section 12 and a second expansion section 13 from one end to the other end, wherein the connecting section is correspondingly positioned at an outlet of an outer ring combustion chamber, high-temperature and high-pressure gas is introduced into the first expansion section 12 and the second expansion section 13 of the movable outer ring nozzle to expand and provide the thrust of an exhaust system in an air suction mode, and an inflection point is arranged at the connecting part of the first expansion section 12 and the second expansion section 13; the main nozzle 2 comprises a main nozzle convergence section 21 and a main nozzle expansion section 22, and the main nozzle convergence section 21 is connected with a rocket thrust chamber or directly used as the rocket thrust chamber to provide the thrust of an exhaust system in a rocket mode; the inner side intersection between the main nozzle convergence section 21 and the main nozzle expansion section 22 is a main nozzle throat 4, the outer ring nozzle throat 5 is formed on the outer wall surface of the main nozzle expansion section 22 and the connection intersection between the connection section 11 and the first expansion section 12, and the connection section 11 and the first expansion section move axially correspondingly to adjust the sectional area of the outer ring nozzle throat 5.
In other embodiments, the diameter of the outer circumference of the main nozzle 2 is gradually increased from the main nozzle convergent section 21 to the main nozzle divergent section 22, and the inner wall surface of the outer ring nozzle connecting section and the outer wall surface of the main nozzle of the section at the corresponding position form an outer ring convergent section.
In other embodiments, the first flared section 12 has an inner diameter dimension corresponding to the larger diameter end that is equal to the inner diameter dimension corresponding to the smaller diameter end of the second flared section 13.
In other embodiments, the main nozzle expanding section 22 is flared, and the outer wall surface thereof sequentially includes an arc section 221 and a straight section 222 corresponding to the central axial direction thereof; the arc radius of the arc segment 221 is larger than the arc radius of the first expansion segment 12; the large-diameter end of the first expansion section 12 is in the same direction as the large-diameter end of the main nozzle expansion section 22.
In other embodiments, the angle between the straight line 222 corresponding to the outer wall surface of the main nozzle expanding section 22 and the central axis is 5-20 °.
Specifically, the diameter of the main nozzle expanding section 22 corresponding to the large-diameter end is larger than the inner diameter of the connecting section 11. So that the outlet of the main nozzle expansion section is located in the first expansion section.
In other embodiments, the profile arcs of the first expanding section 12 and the second expanding section 13 are both determined by a second-order parabola, and an included angle between an outlet tangent of the first expanding section 12 corresponding to the air injection direction and a horizontal line is 0-45 degrees; the second expansion section 13 is corresponding to the exit tangent line of the air injection direction and is 0 ~ 15 with the horizontal line contained angle.
Specifically, in the air intake mode, air enters from an air inlet of the engine, is pressurized by a supercharger, and is ejected from an outer ring nozzle through an outer ring combustion chamber at normal temperature, and in the rocket mode, the air is combusted and expanded through an inner main thrust chamber to form high-temperature gas which is ejected from a main nozzle. Specifically, the fuel gas enters the outer ring connecting section from the outlet of the outer ring combustion chamber, and the fuel gas enters different modes under different air injection modes and is respectively connected to the main nozzle convergence section and the outer ring connecting section.
The jet pipe works in an air suction mode under the condition of low-altitude flight, fuel gas passes through the outer ring jet pipe throat, the outer ring connecting section, the first expansion section and the second expansion section are expanded and accelerated, the outer ring jet pipe throat area is changed by driving the front and back axial movement of the outer ring jet pipe through the actuating and adjusting system, and then the flow change of the jet pipe in the air suction mode is controlled. The discontinuity between the first expansion section and the second expansion section forms an inflection point, so that the separation of air flow at the inflection point is ensured when the spray pipe works at a low pressure drop ratio in an air suction mode, and the excessive expansion of the air flow is prevented, wherein the excessive expansion refers to a state that the static pressure of the air flow expanded in the spray pipe to the outlet section is smaller than the external atmospheric pressure, and a strong shock wave is generated in a pipe opening or the pipe in the state, so that the thrust loss is serious finally.
And when the pressure drop ratio is high, the airflow continues to expand to the outlet of the spray pipe along the second expansion section of the outer ring spray pipe, so that the thrust performance under the high pressure drop ratio is ensured. Under the condition of high-altitude flight, the jet pipe works in a rocket mode, and the fuel gas expands and accelerates in the main jet pipe and the outer ring expansion section and generates thrust. The spray pipe designed by the invention effectively ensures high thrust performance of the spray pipe in a wide pressure drop ratio range and throat area adjusting capacity in an air suction mode by controlling the conversion of the flow separation position and the working mode.
The air-breathing mode refers to exhausting with an outer annular nozzle, and the rocket mode refers to exhausting with a central nozzle. The outer ring spray pipe is correspondingly connected to the outer ring thrust chamber, the main spray pipe corresponds to the main thrust chamber, and the spray pipe works in an air suction mode under the low-altitude flight condition.
Specifically, the main nozzle expansion section extends to the outlet of the main nozzle, the axial position of the outlet of the main nozzle is close to the downstream of the axial position of the throat of the outer ring nozzle, and the downstream is relative to the air injection direction.
The inner diameter of the main nozzle convergent section 21 is gradually reduced, the convergence angle of the main nozzle convergent section can be 15-30 degrees, the area of the throat 4 of the main nozzle is determined according to the fuel gas mass flow of the rocket thrust chamber, the main nozzle convergent section can be designed into a truncated bell-shaped nozzle, and the truncation length is determined according to the area of the outlet 6 of the main nozzle. The main nozzle outlet 6 can be designed according to the radius of the outer ring connecting section, and the radius of the main nozzle outlet 6 is ensured to be larger than or equal to the radius of the outer ring nozzle connecting section 11. The molded surface of the outer wall surface of the main nozzle is simultaneously used as the molded surfaces of the inner wall surfaces of the convergence section and the first expansion section of the outer ring nozzle, wherein the circular arc section of the outer wall surface of the main nozzle is in tangent connection with the straight line section of the outer wall surface of the main nozzle and is used for determining the position and the area of the throat of the outer ring nozzle, and the included angle between the straight line section of the outer wall surface of the main nozzle and the central shaft ranges from 5 degrees to 20 degrees.
The connecting section of the outer ring nozzle is a straight cylinder which is easy to process, is convenient to be connected with a combustion chamber in an air suction mode, and can realize the axial adjusting function of the actuating adjusting system 3. The area influencing factors of the outer ring nozzle throat comprise the inner diameter of the first expansion section and the outer diameter of the main nozzle expansion section, so that the area of the outer ring nozzle throat can be conveniently determined.
Specifically, the area between the intersection of the first expansion section and the connecting section and the outer wall surface of the main nozzle corresponding to the axial position of the first expansion section and the connecting section is the minimum, so that the throat of the outer ring nozzle can be ensured to be the minimum area of outer ring circulation. In the position shown in fig. 1, the throat area of the outer ring nozzle needs to be ensured to be the maximum flow demand area in each state of the air suction mode, for the states in other air suction modes, after the required throat area is determined through the flow of the combustion chamber, the axial position of the movable outer ring nozzle is adjusted through the actuating adjusting system 3, and then the minimum flow area of the outer ring can be reduced, and the area demand of the throat of the outer ring nozzle in different states of the air suction mode is realized.
Specifically, in order to shorten the length of the nozzle, after determining the cross-sectional area at the inflection point of the movable outer ring nozzle, the cross-sectional area at the outlet 7 of the movable outer ring nozzle and the corresponding design point pressure ratio according to the flight envelope of the aircraft, the first expansion section and the second expansion section can be designed according to a bell-shaped nozzle, and in order to give consideration to the maximum axial thrust and the length of the nozzle, the length of the expansion section is generally selected to be 70% -80% of the length of the conical nozzle with the expansion angle of 15 degrees and the same expansion area ratio.
Referring to fig. 3, a section at an inflection point between the first expansion section and the second expansion section of the outer ring nozzle is caused by a difference between an exit tangent angle of the first expansion section and an entrance tangent angle of the second expansion section, and an entrance tangent angle of the movable outer ring second expansion section 13 can be calculated by solving the following formula according to the designed mach numbers of the section at the inflection point of the outer ring nozzle and the section of the outer ring nozzle exit 7:
θ0＝θi+α(ν17-ν16) (1)
wherein alpha is an over-expansion coefficient, and the value of alpha is generally 1.0-2.0, so that the stable separation of the airflow from the inflection point and the wall surface is ensured under the pressure drop ratio of a first design point;
θirepresenting the exit tangent angle of the first flared section;
θ0representing the entry tangent angle of the second flared section; ma16 represents the first design point outlet Mach number of the double-bell-shaped nozzle, and Ma17 represents the second design point Mach number of the double-bell-shaped nozzle;
v16a plantt-meier flow angle corresponding to the first design point;
v17the planter-meier flow angle corresponding to the second design point.
When the engine works in a rocket mode, the outer ring spray pipe 1 can be moved to the position with the smallest throat area of the outer ring spray pipe by using the actuating adjusting system 3, so that the total pressure loss of fuel gas in the rocket mode caused by overhigh step at the outlet 6 of the main spray pipe is reduced, and the thrust performance of the spray pipe in the rocket mode is further improved.
Specifically, with reference to fig. 1, the operating mach number range of the combined power adjustable nozzle with the double expansion sections in a certain air suction mode is 0-5 Ma, the operating pressure ratio range is 11-750, the area change rule of the outer ring nozzle throat required in each state is determined according to the design parameters of the engine, and the required outer ring nozzle throat area is maximally present under the Ma4 working condition and is minimally present under the Ma0 working condition. The throat area of the outer ring spray pipe at the position shown in figure 1 is selected as the area required under the working condition of Ma4, the throat area of the outer ring spray pipe can be reduced by actuating the adjusting system to adjust the outer ring spray pipe rightwards, and then the flow requirements under different working conditions are met.
FIG. 4 is a comparison of the flow characteristics of the composite power variable nozzle of the present invention with dual diverging sections and a bell-shaped nozzle design having the same exit area, wherein the x-axis represents Mach number; the Y-axis represents the flow coefficient; bell nozzle represents a Bell-shaped nozzle, and Dual Bell-Dual model nozzle represents a combined dynamic adjustable nozzle with double expansion sections; it can be obviously seen that the combined power adjustable nozzle with the double expansion sections keeps a flow coefficient of more than 0.98 in a wide flight speed range and is well matched with the state of an engine.
The outlet tangent angle of the first mobile outer ring expansion segment is 6.4 degrees as calculated by the quadratic curve with the form of y ═ c1x2+ c2x + c3, and the inlet tangent angle of the second movable outer ring expansion segment is 33.0 degrees as calculated by the formulas (1), (2) and (3) by selecting the coefficient of over expansion α ═ 1.8.
For the ground takeoff state, the Mach number is artificially set to be 0, thrust coefficients of the combined power adjustable nozzle with the double expansion sections and a bell-shaped nozzle designed with the same area ratio are respectively calculated, the thrust coefficient of the combined power adjustable nozzle with the double expansion sections is 0.952, the thrust coefficient of the bell-shaped nozzle is only 0.814, unstable flow separation is caused by the severe over-expansion phenomenon in the bell-shaped nozzle, and the safety and the stability of the operation of the nozzle are damaged along with severe lateral loads. The combined power adjustable spray pipe with the double expansion sections has the advantages that as the expansion sections are designed into the double-bell-shaped double-expansion-section structure, the fuel gas is stably separated at the inflection points of the outer ring spray pipe, the generation of serious over-expansion is avoided, and the thrust performance is higher. Meanwhile, the outer ring spray pipe is axially moved backwards by using the dynamic adjusting system in the rocket mode, so that the step loss at the outlet of the main spray pipe is reduced, and the thrust efficiency of the main spray pipe can be improved by 2%.
For the device and the using method disclosed by the embodiment, the description is simple because the device and the using method correspond to the method disclosed by the embodiment, and the relevant points can be referred to the description of the method part.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. A combined power adjustable nozzle with double expansion sections, which is installed on an aircraft engine, is characterized by comprising an outer ring nozzle (1) and a main nozzle (2), wherein the outer ring nozzle (1) is positioned on the outer peripheral side of the main nozzle (2), the outer ring nozzle (1) is slidably connected to an engine body through an actuating adjusting system (3) at a tail nozzle of an aerospace engine, a hydraulic cylinder and a servo mechanism of the actuating adjusting system adjust the axial movement of the outer ring nozzle (1), and the main nozzle (2) is communicated with a thrust chamber of the engine; the outer ring nozzle (1) sequentially comprises a connecting section (11), a first expansion section (12) and a second expansion section (13) from one end to the other end, and an inflection point is arranged at the joint of the first expansion section (12) and the second expansion section (13); the main nozzle (2) comprises a main nozzle convergence section (21) and a main nozzle expansion section (22), the inner side intersection between the main nozzle convergence section (21) and the main nozzle expansion section (22) is a main nozzle throat (4), an outer ring nozzle throat (5) is formed on the outer wall surface of the main nozzle expansion section (22) at the connection intersection of the connection section (11) and the first expansion section (12), and the cross section of the outer ring nozzle throat (5) is adjusted by the connection section (11) and the first expansion section through corresponding axial movement.
2. The combined power variable nozzle with double expansion sections as claimed in claim 1, characterized in that the diameter of the outer circumference of the main nozzle (2) is gradually increased corresponding to the direction from the main nozzle convergent section (21) to the main nozzle expansion section (22).
3. A composite power variable nozzle with dual diverging sections according to claim 1, characterised in that the inner diameter of the corresponding large-diameter end of the first diverging section (12) is equal to the inner diameter of the corresponding small-diameter end of the second diverging section (13).
4. The combined power variable nozzle with the double divergent sections as claimed in claim 1, wherein the main nozzle divergent section (22) is trumpet-shaped, and the outer wall surface thereof comprises an arc-shaped section (221) and a straight line section (222) in sequence corresponding to the central axial direction thereof; the arc-shaped half-diameter of the arc-shaped section (221) is larger than that of the first expansion section (12); the large-caliber end of the first expansion section (12) and the large-caliber end of the main nozzle expansion section (22) are in the same direction.
5. The combined power variable nozzle with the double divergent sections as claimed in claim 4, characterized in that the included angle between the straight line section (222) corresponding to the outer wall surface of the main nozzle divergent section (22) and the central axis is 5-20 °.
6. The combined power variable nozzle with double diverging sections as claimed in claim 1, wherein the diameter dimension of the main nozzle diverging section (22) corresponding to the large-diameter end is larger than the inner diameter dimension of the connecting section (11).
7. The combined power variable nozzle with the double expansion sections as claimed in claim 1, characterized in that the profile arcs of the first expansion section (12) and the second expansion section (13) are both determined by a second-order parabola, and the included angle between the outlet tangent of the first expansion section (12) corresponding to the air injection direction and the horizontal line is 0-45 °; the second expansion section (13) is corresponding to the outlet tangent line of the air injection direction and forms an included angle of 0-15 degrees with the horizontal line.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111319546.XA CN114046211A (en) | 2021-11-09 | 2021-11-09 | Combined power adjustable spray pipe with double expansion sections |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111319546.XA CN114046211A (en) | 2021-11-09 | 2021-11-09 | Combined power adjustable spray pipe with double expansion sections |
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| CN114046211A true CN114046211A (en) | 2022-02-15 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114776465A (en) * | 2022-05-25 | 2022-07-22 | 厦门大学 | Adjustable plug type spray pipe based on rotary detonation engine |
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| BE602122R (en) * | 1960-04-01 | 1961-07-17 | Gen Electric | Adjustable convergent-divergent nozzle |
| US5052176A (en) * | 1988-09-28 | 1991-10-01 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Combination turbojet-ramjet-rocket propulsion system |
| WO2008129372A2 (en) * | 2007-04-24 | 2008-10-30 | Moscow Aviation Institute | Rocket engine laval nozzle with gas injection device |
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| CN106286012A (en) * | 2016-09-18 | 2017-01-04 | 北京航天动力研究所 | A kind of suction type rocket combination power device |
| CN108999725A (en) * | 2018-07-19 | 2018-12-14 | 北京航空航天大学 | A kind of nozzles with injector of the double bell injection casings of band |
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2021
- 2021-11-09 CN CN202111319546.XA patent/CN114046211A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE602122R (en) * | 1960-04-01 | 1961-07-17 | Gen Electric | Adjustable convergent-divergent nozzle |
| US5052176A (en) * | 1988-09-28 | 1991-10-01 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Combination turbojet-ramjet-rocket propulsion system |
| WO2008129372A2 (en) * | 2007-04-24 | 2008-10-30 | Moscow Aviation Institute | Rocket engine laval nozzle with gas injection device |
| CN105637208A (en) * | 2013-10-11 | 2016-06-01 | 喷气发动机有限公司 | A nozzle arrangement for an engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114776465A (en) * | 2022-05-25 | 2022-07-22 | 厦门大学 | Adjustable plug type spray pipe based on rotary detonation engine |
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