CN117905582A - Single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and switching method thereof - Google Patents
Single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and switching method thereof Download PDFInfo
- Publication number
- CN117905582A CN117905582A CN202410168905.3A CN202410168905A CN117905582A CN 117905582 A CN117905582 A CN 117905582A CN 202410168905 A CN202410168905 A CN 202410168905A CN 117905582 A CN117905582 A CN 117905582A
- Authority
- CN
- China
- Prior art keywords
- pressure section
- section
- channel
- profile
- air inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 4
- 230000006835 compression Effects 0.000 claims description 11
- 238000007906 compression Methods 0.000 claims description 11
- 238000002485 combustion reaction Methods 0.000 abstract description 33
- 238000013461 design Methods 0.000 description 7
- 238000002955 isolation Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 3
- 230000008602 contraction Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Landscapes
- Characterised By The Charging Evacuation (AREA)
Abstract
The invention discloses a single-double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and a switching method thereof, wherein the air inlet channel comprises an external pressure section, an internal pressure section, a flow dividing plate and an expansion section, the flow dividing plate is arranged between a lip cover and a lower molded surface of the expansion section and is parallel to the lower end surface of the lip cover, the length of the flow dividing plate is equal to the length of the expansion section, and the expansion section is divided into two flow dividing channels; one end of the lower profile of the inner pressure section, which is positioned at the upstream, is rotationally connected with one end of the outer pressure section, which is positioned at the downstream, through a rotating shaft; the rotating shaft is provided with a locking device, and when in operation, the lower part of the lower molded surface of the inner pressure section and the lower molded surface of the expansion section or the splitter plate are smoothly connected, the lower molded surface of the inner pressure section and the outer pressure section molded surface can be locked, so that the inner pressure section and the outer pressure section molded surface cannot rotate relatively. According to the invention, through single-channel and double-channel switching, the matching with two different working modes of the sub-combustion and the super-combustion of the downstream ramjet engine is realized, the throat height of the air inlet channel can be controlled, and the air inlet channel designed according to high Mach number can be smoothly started under low Mach number.
Description
Technical Field
The invention relates to the field of design of variable geometry methods of hypersonic wide-speed-range air inlets, in particular to a single-channel and double-channel switching type binary hypersonic variable geometry air inlet and a switching method thereof.
Background
The wide-speed-range hypersonic-speed air suction type aircraft requires that the air inlet channel can work under wider working conditions, and the air inlet channel working in a fixed-geometry mode cannot realize wide-range stable air inlet of the aircraft. When the wide-speed-domain hypersonic air inlet channel works at the Ma=2-10 level, when the Mach number of the designed working point is higher, the phenomenon of no starting exists under the working condition of low Mach number, such as the working condition of incoming flow Mach number Ma=2-3, and then a variable geometry adjusting means is required to be introduced. Meanwhile, when the working speed range of the aircraft is wider, the ramjet engine may have the mode conversion requirement of converting the sub-combustion mode into the super-combustion mode, the sub-combustion mode often requires that the post-expansion section of the throat of the air inlet channel continuously compresses the post-end-excited sub-sonic airflow, and the super-combustion mode requires that the post-expansion section of the throat of the air inlet channel is set to be an equal-area section or a small-expansion-angle molded surface, which is called an isolation section.
The variable geometry method for solving the starting problem of the air inlet is generally to enlarge the area of the throat of the air inlet, and for the air inlet working at hypersonic speed, the rear profile section of the throat of the air inlet is called an isolation section, which is generally an equal area profile or is required to have a smaller expansion angle, so that the throat can not be expanded to a larger extent without controlling the combustion chamber to carry out matched adjustment. The high-temperature hypersonic-flow-rate combustion chamber has the advantages that the air flow speed in the combustion chamber suitable for hypersonic flow is high, the temperature is high, the combustion chamber is subjected to severe tests of structural problems and thermal problems, if the mechanical adjustment is carried out on the combustion chamber, the problems of difficult processing and high mechanical adjustment cost exist in engineering, and the possibility of engineering implementation is low.
Therefore, a high-feasibility geometric method is required to be provided to avoid excessive mechanical adjustment, so that the starting problem of the air inlet channel can be solved, the stable and normal operation of the air inlet channel in a wide-speed range can be ensured, the matching with different working modes of a combustion chamber can be realized, and the performance of the air inlet channel can be improved.
Disclosure of Invention
The invention aims to solve the technical problems of no starting of a wide-speed-range air inlet channel with the characteristics of equal area or small expansion angle isolation section in a low Mach number working range at a hypersonic design point and matching of different modes with a combustion chamber of a ramjet engine in the background art, and provides a single-channel and double-channel switching type binary hypersonic variable geometry air inlet channel and a switching method thereof.
The invention adopts the following technical scheme for solving the technical problems:
the single-double-channel switching type binary high-ultrasonic-speed variable-geometry air inlet channel comprises an external pressure section, an internal pressure section, a splitter plate and an expansion section;
The flow dividing plate is arranged between the lip cover of the expansion section and the lower molded surface, is parallel to the lower end surface of the lip cover, has the same length as the expansion section, and divides the expansion section into two flow dividing channels, wherein the flow dividing channels with the same cross section area are formed between the flow dividing plate and the lip cover of the expansion section, and the flow dividing channels with the outlet cross section area larger than the inlet cross section area are formed between the flow dividing plate and the lower molded surface of the expansion section;
one end of the lower profile of the inner pressure section, which is positioned at the upstream, is rotationally connected with one end of the outer pressure section, which is positioned at the downstream, through a rotating shaft; the rotating shaft and the external pressure section profile are coplanar and perpendicular to the air inlet flow direction;
and a locking device is arranged on the rotating shaft and used for locking the lower profile of the inner pressure section and the outer pressure section profile when the lower stream of the lower profile of the inner pressure section is smoothly connected with the lower profile of the expansion section or the splitter plate, so that the lower profile of the inner pressure section and the outer pressure section profile cannot rotate relatively.
As a further optimization scheme of the single-double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel, the external pressure section adopts a curved surface compression type molded surface.
The invention also discloses a switching method of the single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel, which is characterized by comprising the following steps of:
if the interval of the incoming flow Mach number of the single-channel and double-channel switching type binary high-ultrasonic variable geometry air inlet channel is [2,4], controlling the lower profile of the inner pressure section to rotate around the rotating shaft relative to the outer pressure section profile, and locking the lower profile of the inner pressure section and the outer pressure section profile when the lower stream of the lower profile of the inner pressure section is smoothly connected with the lower profile of the expansion section, so that the lower profile and the outer pressure section profile cannot rotate relatively;
If the interval of the incoming flow Mach number of the single-channel and double-channel switching type binary high-ultrasonic variable geometry air inlet channel is [5, 10], the lower profile of the inner pressure section is controlled to rotate around the rotating shaft relative to the outer pressure section profile, and the lower profile of the inner pressure section and the outer pressure section profile are locked when the downstream of the lower profile of the inner pressure section is smoothly connected with the splitter plate, so that the inner pressure section and the outer pressure section profile cannot rotate relatively.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
1. The invention solves the starting problem of the air inlet with a high Mach number design point at a low Mach number by constructing an air inlet variable geometry mode of single-flow and double-flow switching type, and greatly widens the stable working speed range of the air inlet. Compared with a prototype air inlet channel with fixed geometry, the air inlet channel has better flow capture in a required working speed range. Compared with other variable geometry schemes, the device avoids the requirement of mechanical adjustment on the combustion chamber, and has the advantages of simple structure and high engineering realizability;
2. The invention realizes the matching of different modes with the ramjet engine through the switching of the single flow channel and the double flow channel. In a low-inflow Mach number working interval, the ramjet engine is in a sub-combustion mode, the air inlet channel is switched to a double-channel mode, and the back of the throat channel is an expansion section generally; in a high-inflow Mach number working interval, the ramjet engine is in a super-combustion mode, the air inlet channel is a single channel with the cross section of equal area, and the back of the throat channel is generally in an equal area section;
3. the invention ensures that the air flow is divided into two flows into the combustion chamber by arranging the flow dividing plate, and the expanded flow dividing flow passage always has smaller air flow velocity under the back pressure forward transmission effect of the air inlet passage, so that low-speed air flow is intensively provided in a limited space, and the invention is potentially beneficial to ignition of the combustion chamber and full combustion of fuel. Meanwhile, the design parameters of the flow dividing channels can be flexibly adjusted according to different requirements of the combustion chambers to provide air flow meeting the performance requirements.
Drawings
FIG. 1 is a schematic two-dimensional cross-sectional view of a fixed geometry inlet;
fig. 2 is a mach number equivalent cloud for a fixed geometry inlet flow mach number ma=2;
fig. 3 is a mach number equivalent cloud for a fixed geometry inlet flow mach number ma=3;
fig. 4 is a mach number equivalent cloud for a fixed geometry inlet flow mach number ma=4;
fig. 5 is a mach number equivalent cloud for a fixed geometry inlet flow mach number ma=8;
fig. 6 is a mach number equivalent cloud for a fixed geometry inlet flow mach number ma=10;
FIG. 7 is a two-dimensional cross-sectional schematic of the present invention;
Fig. 8 is a mach number contour plot for the incoming stream mach number ma=2 of the present invention;
Fig. 9 is a mach number contour plot for the incoming stream mach number ma=3 of the present invention;
fig. 10 is a mach number contour plot for the incoming stream mach number ma=4 of the present invention;
FIG. 11 is a graph showing flow coefficient random flow Mach number curve versus a fixed geometry inlet.
In the figure, the profile of the 1-external pressure section, the 2-lower profile of the internal pressure section in the double-channel mode, the 3-lower profile of the expansion section, the 4-lip cover, the 5-splitter plate, the 6-c, the 7-lower profile of the internal pressure section in the single-channel mode, the throat of the 8-single-channel mode, the split flow channel between the 9-splitter plate and the lip cover of the expansion section, the split flow channel between the 10-splitter plate and the lower profile of the expansion section, and the 11-rotating shaft.
Detailed Description
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the components are exaggerated for clarity.
As shown in FIG. 7, the invention discloses a single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel, which comprises an external pressure section, an internal pressure section, a splitter plate and an expansion section;
The flow dividing plate is arranged between the lip cover of the expansion section and the lower molded surface, is parallel to the lower end surface of the lip cover, has the same length as the expansion section, and divides the expansion section into two flow dividing channels, wherein the flow dividing channels with the same cross section area are formed between the flow dividing plate and the lip cover of the expansion section, and the flow dividing channels with the outlet cross section area larger than the inlet cross section area are formed between the flow dividing plate and the lower molded surface of the expansion section;
one end of the lower profile of the inner pressure section, which is positioned at the upstream, is rotationally connected with one end of the outer pressure section, which is positioned at the downstream, through a rotating shaft; the rotating shaft and the external pressure section profile are coplanar and perpendicular to the air inlet flow direction;
and a locking device is arranged on the rotating shaft and used for locking the lower profile of the inner pressure section and the outer pressure section profile when the lower stream of the lower profile of the inner pressure section is smoothly connected with the lower profile of the expansion section or the splitter plate, so that the lower profile of the inner pressure section and the outer pressure section profile cannot rotate relatively.
The invention also discloses a switching method of the single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel, which is characterized by comprising the following steps of:
if the interval of the incoming flow Mach number of the single-channel and double-channel switching type binary high-ultrasonic variable geometry air inlet channel is [2,4], controlling the lower profile of the inner pressure section to rotate around the rotating shaft relative to the outer pressure section profile, and locking the lower profile of the inner pressure section and the outer pressure section profile when the lower stream of the lower profile of the inner pressure section is smoothly connected with the lower profile of the expansion section, so that the lower profile and the outer pressure section profile cannot rotate relatively;
If the interval of the incoming flow Mach number of the single-channel and double-channel switching type binary high-ultrasonic variable geometry air inlet channel is [5, 10], the lower profile of the inner pressure section is controlled to rotate around the rotating shaft relative to the outer pressure section profile, and the lower profile of the inner pressure section and the outer pressure section profile are locked when the downstream of the lower profile of the inner pressure section is smoothly connected with the splitter plate, so that the inner pressure section and the outer pressure section profile cannot rotate relatively.
The external pressure section is preferably a curved surface compression type surface, and gradually bends outwards along the flow direction from the front edge starting compression angle to form a curved surface configuration, and under the supersonic velocity incoming flow condition, curved surface compression shock waves are generated to be matched with the lip of the air inlet channel, so that the external pressure section has higher flow capturing capacity in a wider Mach number change range.
The internal pressure section realizes single-flow and double-flow channel mode switching by rotating the lower molded surface of the internal pressure section, and meanwhile, the flow area of a throat channel of the internal pressure section can be adjusted, so that the flow capacity of the air inlet channel under a lower Mach number is ensured; the compatibility of compression under high Mach number and starting under low Mach number is realized through rotation adjustment, and the stable operation of the wide speed range of the air inlet channel is ensured;
The expansion section is connected with the downstream sudden expansion type combustion chamber, when the high Mach number ramjet engine works in the super-combustion mode, the lower molded surface of the internal pressure section closes the flow passage between the flow dividing plate and the lower molded surface of the expansion section through rotation, and the air inlet passage is in a single flow passage mode at the moment, has higher internal contraction ratio and is matched with the super-combustion working mode of the downstream combustion chamber.
When the low Mach number ramjet engine works in a sub-combustion mode, the lower molded surface of the inner pressure section opens the flow passage between the flow dividing plate and the lower molded surface of the expansion section through rotation, the throat is increased, and at the moment, the air inlet channel is in a double-flow-passage mode, and has a lower internal contraction ratio and is matched with the sub-combustion working mode of the downstream combustion chamber.
The invention discards the traditional internal flow air inlet layout of single-channel air inlet and provides a single-channel and double-channel switching type variable geometry adjustment mode. In the prior art, when aiming at an air inlet channel with an equal area or an isolation section with a smaller expansion angle, effective control on the throat height or the flow area cannot be realized under the condition that the combustion chamber is not required to be matched with mechanical adjustment. According to the invention, the single-flow and double-flow-channel working mode switching is realized by rotating and adjusting the partial molded surface of the inner compression section, so that the air inlet channel has throat characteristics which are suitable for the working mode of the combustion chamber and an expansion section/equal-area isolation section behind the throat in different Mach number ranges, and the problem of no starting of the low-inflow Mach number working condition is solved.
As shown in fig. 1, a binary curved surface compression air inlet with a fixed geometric design is provided, the working range of the air inlet is ma=2-10, the flying height is 10.93-31.79km, the incoming flow Mach number of a selected design point is ma=8, the flying height is 28.79km, and the isolation section behind the throat of the air inlet is an equal-area section.
Fig. 2, 3, 4,5 and 6 show the mach number cloud diagrams obtained by the numerical simulation of the working conditions of the binary fixed geometry air inlet channel when the incoming flow mach numbers ma=2, 3, 4, 8 and 10 respectively. When the Mach number Ma=10 of the fixed geometry air inlet is reached, the curved shock waves are emitted into the lip cover, and the air inlet is in an over-rated working condition at the moment, so that the air inlet can still normally enter air. The incoming flow Mach number is Ma=8 working condition, and at the moment, the hypersonic incoming flow is compressed through the curved compression profile to form an external compression curved shock wave injection position at the front edge of the lip cover. The fixed geometry air inlet is not started at ma=2 and ma=3, the capturing capacity of the air inlet on the flow in the state suddenly drops, and sufficient air flow cannot be provided for normal operation of the aircraft.
When the air inlet channel is in a double-channel working mode, air flow enters the combustion chamber through the two split flow channels; when the air inlet channel is switched to a single-channel working mode, air flows flow flows into the combustion chamber through the split flow channel between the split flow plate and the lip cover of the expansion section, and the throat in the double-channel mode and the throat in the single-channel mode are shown in fig. 7.
A specific variable geometry implementation is: in the low Mach number range (Ma=2-4), the air inlet is in a double-flow-channel mode, and the throat of the double-flow-channel mode is 40.5991mm. The air flows at this time are split by the splitter plates and then respectively flow into the two splitter runners and then enter the combustion chamber. As the incoming flow mach number further increases to the high mach number range (ma=5-10), the lower profile of the inner compression section is rotated counter-clockwise about the axis of rotation, placing the inlet in a single flow channel mode. The throat in the single-flow mode was 29mm at this time. The air flow only flows into the combustion chamber through the flow dividing flow passage between the flow dividing plate and the lip shroud of the diverging section.
Fig. 8, 9, and 10 correspond to the mach number contour maps obtained by numerical simulation when the inlet port is switched to the dual-flow mode in the low mach number operation interval (ma=2-4) when ma=2, ma=3, and ma=4, respectively. After the double-flow-channel mode is switched, as can be seen in the figure, the throat flow area of the air inlet channel is expanded, so that air flow can smoothly flow into the air inlet channel at ma=2-3, and congestion of the inner flow channel of the air inlet channel is avoided.
FIG. 11 is a graph of flow coefficient variation for a fixed geometry inlet and a single/dual flow switching variable geometry inlet under different incoming Mach numbers, with the abscissa representing the incoming Mach number and the ordinate representing the inlet flow capture coefficient. The single-channel and double-channel switching type variable geometry method solves the problem that the fixed geometry design air inlet channel is not started in Ma2 and Ma 3.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (3)
1. The single-double-channel switching type binary high-ultrasonic-speed variable-geometry air inlet channel comprises an external pressure section, an internal pressure section and an expansion section, and is characterized by further comprising a flow dividing plate;
The flow dividing plate is arranged between the lip cover of the expansion section and the lower molded surface, is parallel to the lower end surface of the lip cover, has the same length as the expansion section, and divides the expansion section into two flow dividing channels, wherein the flow dividing channels with the same cross section area are formed between the flow dividing plate and the lip cover of the expansion section, and the flow dividing channels with the outlet cross section area larger than the inlet cross section area are formed between the flow dividing plate and the lower molded surface of the expansion section;
One end of the lower profile of the inner pressure section, which is positioned at the upstream, is rotationally connected with one end of the outer pressure section, which is positioned at the downstream, through a rotating shaft, so that the lower profile of the inner pressure section can rotate around the rotating shaft freely relative to the outer pressure section; the rotating shaft and the external pressure section profile are coplanar and perpendicular to the air inlet flow direction;
and a locking device is arranged on the rotating shaft and used for locking the lower profile of the inner pressure section and the outer pressure section profile when the lower stream of the lower profile of the inner pressure section is smoothly connected with the lower profile of the expansion section or the splitter plate, so that the lower profile of the inner pressure section and the outer pressure section profile cannot rotate relatively.
2. The single-dual flow switching binary high ultrasonic variable geometry inlet of claim 1, wherein the outer pressure section is a curved compression profile.
3. The method for switching the single-double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel based on claim 1 is characterized by comprising the following steps:
if the interval of the incoming flow Mach number of the single-channel and double-channel switching type binary high-ultrasonic variable geometry air inlet channel is [2,4], controlling the lower profile of the inner pressure section to rotate around the rotating shaft relative to the outer pressure section profile, and locking the lower profile of the inner pressure section and the outer pressure section profile when the lower stream of the lower profile of the inner pressure section is smoothly connected with the lower profile of the expansion section, so that the lower profile and the outer pressure section profile cannot rotate relatively;
If the interval of the incoming flow Mach number of the single-channel and double-channel switching type binary high-ultrasonic variable geometry air inlet channel is [5, 10], the lower profile of the inner pressure section is controlled to rotate around the rotating shaft relative to the outer pressure section profile, and the lower profile of the inner pressure section and the outer pressure section profile are locked when the downstream of the lower profile of the inner pressure section is smoothly connected with the splitter plate, so that the inner pressure section and the outer pressure section profile cannot rotate relatively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410168905.3A CN117905582A (en) | 2024-02-06 | 2024-02-06 | Single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and switching method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410168905.3A CN117905582A (en) | 2024-02-06 | 2024-02-06 | Single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and switching method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117905582A true CN117905582A (en) | 2024-04-19 |
Family
ID=90690866
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410168905.3A Pending CN117905582A (en) | 2024-02-06 | 2024-02-06 | Single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and switching method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117905582A (en) |
-
2024
- 2024-02-06 CN CN202410168905.3A patent/CN117905582A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5121440B2 (en) | Convertible gas turbine engine | |
| US8281588B2 (en) | Turbomachine system and turbine therefor | |
| US8522547B2 (en) | Exhaust gas turbocharger for an internal combustion engine of a motor vehicle | |
| CN112727635B (en) | Double-culvert engine | |
| US20170370290A1 (en) | Gas turbine engine | |
| CN111102098B (en) | Turbojet propulsion system based on front-mounted compression guide impeller and control method | |
| JP2006097684A (en) | Multi-stage turbo supercharger using vtg turbine stage | |
| CN114439646B (en) | Air turbine rocket stamping combined propulsion system | |
| CN113236424B (en) | Double-lower-side rear supersonic air inlet | |
| CN106168185A (en) | Air turbine punching press combined engine and method of work thereof | |
| CN209800119U (en) | Self-driven outer duct contra-rotating annular fan blade compression device | |
| CN117905582A (en) | Single-channel and double-channel switching type binary high-ultrasonic-speed variable geometry air inlet channel and switching method thereof | |
| CN112780441B (en) | Variable flow passage ramjet engine and design and adjustment method | |
| CN117028059A (en) | Separate exhaust throat offset type pneumatic vector spray pipe based on variable cycle engine | |
| CN113153577B (en) | Multistage rotary detonation rocket stamping combined engine | |
| CN114856856B (en) | High-rise-limit low-oil-consumption medium-bypass-ratio variable-cycle engine | |
| CN113864050B (en) | Detonation supercharging aircraft engine | |
| CN113464280B (en) | Controllable air inlet channel based on leakage gap switch and method | |
| CN209800118U (en) | Self-driven outer duct annular fan blade compression device | |
| CN113864053A (en) | Ma 4-grade supersonic axisymmetric air inlet and method based on adjustable leakage flow gap | |
| CN114046211A (en) | Combined power adjustable spray pipe with double expansion sections | |
| US20200200107A1 (en) | Twin-scroll turbine with flow control valve | |
| CN114576006B (en) | Engine and aircraft | |
| CN114623019B (en) | Large-bypass-ratio split type variable-circulation turbofan engine | |
| CN114320660B (en) | Wide-speed-range ramjet engine based on axial ultrasonic incoming flow variable geometry fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |