CN110645099A - Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet - Google Patents
Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet Download PDFInfo
- Publication number
- CN110645099A CN110645099A CN201910963940.3A CN201910963940A CN110645099A CN 110645099 A CN110645099 A CN 110645099A CN 201910963940 A CN201910963940 A CN 201910963940A CN 110645099 A CN110645099 A CN 110645099A
- Authority
- CN
- China
- Prior art keywords
- section
- channel
- splitter plate
- central cone
- mach number
- 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.)
- Granted
Links
- 230000008602 contraction Effects 0.000 claims abstract description 28
- 238000002485 combustion reaction Methods 0.000 claims abstract description 16
- 230000035939 shock Effects 0.000 claims abstract description 10
- 238000007789 sealing Methods 0.000 claims abstract description 8
- 238000013519 translation Methods 0.000 claims abstract description 7
- 238000005507 spraying Methods 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims 4
- 230000003247 decreasing effect Effects 0.000 claims 1
- 238000004080 punching Methods 0.000 claims 1
- 238000013461 design Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
Abstract
The invention discloses a Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet channel which mainly comprises a fixed lip cover profile, a front-back translation central cone and a splitter plate component, wherein a turbojet channel and a sub-combustion stamping channel are formed, and the two channels are always in an open state in the range of Mach number 0-5 +. The Mach number of the accompanying current rises, the central cone horizontally moves forward to ensure a high flow coefficient in a wide range, shock wave sealing is realized when the Mach number is more than Ma2, and the flow coefficient of an air inlet channel is kept at 1.0; the splitter plate is linked with the central cone, so that the contraction ratio of the two channels of the vortex spraying and the stamping is increased along with the increase of the Mach number, and the flow distribution of the two channels is adjusted according to requirements. In a distance, the maximum windward area of the air inlet is obviously increased along the way compared with the capture area.
Description
Technical Field
The invention belongs to the technical field of aerospace craft super air inlet and outlet systems, and particularly relates to a Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet channel.
Background
The air inlet channel is an important component of an air-breathing engine, and the flow capture coefficient of the air inlet channel is one of key performance parameters of the air inlet channel. The performance of a traditional fixed-geometry air inlet reaches an expected requirement at a design point, but in a non-design point state, shock waves at the head of the air inlet are greatly changed, so that the capacity of capturing flow is greatly reduced, and therefore the traditional fixed-geometry air inlet cannot always provide enough required flow for an engine when working in a wide Mach number range. In a wide-range precooling and stamping combined engine, a turbojet channel is in a working state under the action of a precooler and under the full working condition of a stamping channel, and in order to meet the performance requirement of the engine, an air inlet channel configuration which can provide sufficient flow for the double channels in a wide working range needs to be matched, and therefore a Ma0-5+ wide-range precooling and stamping combined engine axisymmetric adjustable air inlet channel is designed.
Disclosure of Invention
Aiming at a Ma0-5+ wide-range precooling and stamping combined engine, the invention provides an axisymmetric adjustable air inlet, wherein a turbojet channel and a stamping channel of the axisymmetric adjustable air inlet can provide sufficient required flow for the engine under the whole working condition, and can meet the performance requirements of the channels under different working conditions.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet channel is composed of a fixed part lip cover, a movable part splitter plate and a movable part center cone from outside to inside in a manner of being symmetrical by a central shaft, wherein the profile of the splitter plate is divided into an inner profile and an outer profile, and the splitter plate is always positioned between the lip cover and the center cone under the full working condition;
the lip cover consists of a tail section with the same width and a front section with the opening gradually reduced;
the front and the back of the flow distribution plate are composed of fan blade sections and horizontal telescopic sections, and the tail end of each horizontal telescopic section is fixed at a support at the tail end of the lip cover; the inner profile of the fan blade section positioned at the front part of the flow distribution plate consists of an expansion section, an equidistant section and a contraction section from inside to outside, and the outer profile of the fan blade section consists of an inner expansion section and an outer contraction section from inside to outside; the flow distribution plate performs front-back telescopic translational motion through the horizontal telescopic section;
the central cone consists of a middle cylindrical section and a front conical section and a rear conical section, and the rear conical section is fixed between the horizontal telescopic sections of the flow distribution plate through a telescopic structure and performs front-rear telescopic translation movement through the telescopic structure;
the central cone and the splitter plate do forward and backward translation motion according to flight working condition requirements, the inner molded surface, the lip cover and the outer molded surface of the central cone and the splitter plate respectively form a vortex spraying channel and a sub-combustion stamping channel which are contracted and expanded firstly, and the two channels are always in an open state in the range of Ma0-5 +.
Further, when the central cone and the splitter plate are completely retracted, the front conical section of the central cone is parallel to the contraction section of the inner molded surface, and the cylindrical section of the central cone is matched with the equidistant section of the inner molded surface; in the advancing process, the minimum flow areas of the turbojet channel and the sub-combustion stamping channel are gradually reduced, and in the process, the horizontal moving distance of the central cone is adjusted according to the incoming flow Mach number to keep shock wave sealing.
Furthermore, the cone section at the rear part of the tail end of the horizontal telescopic section of the flow distribution plate is fixed on the vertical support frame between the horizontal telescopic sections of the flow distribution plate through a sleeve structure, and the front and the rear telescopic translational motion is carried out.
Furthermore, as the Mach number of the incoming current increases, the central cone horizontally moves forward to ensure a high flow coefficient in a wide range, shock wave sealing is realized when the flow rate is more than Ma2, the central cone horizontally moves forward to ensure shock wave sealing in the wide range, and the flow coefficient of an air inlet channel is kept at 1.0; the movable part splitter plate is linked with the central cone and moves forwards horizontally at the same time, so that the contraction ratios of the turbojet channel and the sub-combustion stamping channel are ensured to be increased along with the increase of the Mach number; horizontally moving the movable part splitter plate to adjust the flow distribution of the turbojet channel and the sub-combustion stamping channel; in the gradually-expanding profile of the front section of the lip cover, the maximum windward area of the air inlet channel is increased along the way compared with the capture area.
Further, under the condition of low Mach number, the relative distance between the splitter plate and the central cone is large, the throat of the turbojet channel is located at the rear position, the contraction ratio is small, and the starting performance of the air inlet channel is met; under the high Mach number, the relative distance between the splitter plate and the central cone is small, the throat of the turbojet channel moves forward, the area is reduced, and the contraction ratio reaches the maximum value.
Further, under the condition of low Mach number, the relative distance between the splitter plate and the lip cover is large, the throat area is large, the contraction ratio is small, and the stamping channel is in a normal starting state; under the high Mach number, the relative distance between the splitter plate and the lip cover is reduced, the throat area reaches the minimum value, the contraction ratio is the maximum, and the incoming flow is decelerated to the throat of the sub-combustion stamping channel and then slowly expanded.
The axial-symmetry adjustable air inlet design has the beneficial effects that the air inlet of the Ma0-5+ wide-range precooling + stamping combined engine has high-flow capture characteristics and compression capacity matched with the high-flow capture characteristics in a wide range, and meets the working requirements of the wide-range high performance of the engine; by designing the inner and outer molded surfaces of the splitter plate and adjusting the positions of the central cone and the splitter plate, the throat area of each channel of the air inlet channel can be changed while flow distribution is realized, so that the contraction ratio is changed, and the air inlet channel can flexibly adapt to wide-range working conditions.
Drawings
FIG. 1 is a schematic diagram of the adjustment of the center cone and the splitter plate of the inlet duct.
Fig. 2 is a schematic view of the connection structure of the central cone and the splitter plate.
FIG. 3 is a schematic view of the inlet duct runner with the center cone at the retracted position.
FIG. 4 is a schematic view of the inlet duct flow path with the center cone at the forward position.
Wherein, 1 lip cover, 2 central cone, 3 splitter plate, 4 splitter plate inner molded surfaces and 5 splitter plate outer molded surfaces.
Detailed Description
The following description will further describe embodiments of the present invention with reference to the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the scheme according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted.
The invention discloses a Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet, wherein a schematic diagram of adjusting a central cone and a splitter plate of the air inlet is shown in figure 1, a schematic diagram of an air inlet channel flow channel with the central cone positioned at a rear shrinkage position is shown in figure 3, and a schematic diagram of an air inlet channel flow channel with the central cone positioned at a front extension position is shown in figure 4.
The axisymmetric adjustable air inlet channel is composed of a fixed part and a movable part, wherein the fixed part is an axisymmetric lip cover 1, and the movable part comprises a central cone 2 and a splitter plate 3. The lip cover 1 consists of a tail section with the same width and a front section with the opening gradually reduced; the front and the back of the flow distribution plate 3 are composed of a fan blade section and a horizontal telescopic section, the horizontal telescopic section realizes front and back telescopic through a sleeve structure, and the sleeve is connected with an external force application unit, such as a hydraulic power system, an electric push rod and the like; the tail end is fixed at the bracket at the tail end of the lip cover 1;
the central cone 2 consists of a middle cylindrical section and a front conical section and a rear conical section, and can move horizontally through a certain adjusting structure, for example, a sleeve structure is adopted to realize translation, and the sleeve is connected with an external force application unit, such as a hydraulic power system, an electric push rod and the like. Specifically, as shown in fig. 2, a vertical support frame is arranged between an upper horizontal telescopic section and a lower horizontal telescopic section of the splitter plate 3, the central cone is connected with the support frame through a sleeve, and the sleeve is translated to drive the central cone 2 to translate. In the same way, the hydraulic rod can be replaced by an actuating system with the same principle.
The splitter plate 3 comprises a splitter plate inner molded surface 4 and a splitter plate outer molded surface 5, the inner molded surface 4 of the fan blade section positioned at the front part of the splitter plate 3 consists of an expansion section, an equidistant section and a contraction section from inside to outside, and the outer molded surface 5 of the fan blade section consists of an inner expansion section and an outer contraction section from inside to outside; the movable part central cone 2 and the movable part flow distribution plate 3 do front and back translation movement according to flight working conditions and flow distribution requirements, and an external force application unit connected with the movable part central cone provides a power source to serve as an actuating system to realize actuation; the central cone 2 and the inner molded surface 4 of the movable part splitter plate form a vortex spraying channel, and the lip cover 1 and the outer molded surface 5 of the movable part splitter plate form a sub-combustion stamping channel; the turbojet channel and the sub-combustion stamping channel are always in an open state in the Ma0-5+ range, the Mach number of the current is increased, the horizontal forward movement of the central cone ensures the shock wave sealing in a wide range, and the flow coefficient of an air inlet channel is kept at 1.0; the splitter plate 3 is linked with the central cone 2 to ensure that the contraction ratios of the turbojet channel and the sub-combustion stamping channel are increased along with the increase of the Mach number, as shown in FIG. 1; the flow of the turbojet channel and the flow of the sub-combustion stamping channel can be distributed as required by horizontally moving the flow distribution plate 3; in the gradually-expanding profile of the front section of the lip cover, the maximum windward area of the air inlet channel is obviously increased along the way compared with the capture area.
As shown in fig. 3, when the air inlet channel is at a low mach number, the relative distance between the splitter plate 3 and the central cone 2 is large, the throat of the turbojet channel is located at a rear position, the contraction ratio is small, and the starting performance of the air inlet channel is met; as shown in fig. 4, at a high mach number, the distance between the splitter plate 3 and the central cone 2 is relatively small, the throat of the turbojet channel moves forward, the area is reduced, and the contraction ratio reaches a maximum value.
Under the condition of low Mach number of the air inlet channel, the relative distance between the flow distribution plate 3 and the lip cover 1 is large, the throat area is large, the contraction is small, and the stamping channel is in a normal starting state; under the high Mach number, the relative distance between the splitter plate 3 and the lip cover 1 is reduced, the throat area reaches the minimum value, the contraction ratio is the maximum, and the incoming flow is decelerated to the throat of the sub-combustion stamping channel and then slowly expanded.
Preferably, in some embodiments, the state point of the highest flight mach number is used as a design point, the shock wave is sealed, the position of the central cone 2 at the moment is determined, and the initial position of the splitter plate 3 is determined according to the flow demand of the two channels at the moment; when various profiles are designed, the contraction ratio of the two channels is reasonable (such as the contraction ratio of a stamping channel is 6.5, and the contraction ratio of a turbine channel is 4.0) under a high Mach number state so as to ensure enough compression amount, and meanwhile, the two channels have certain starting performance under a low Mach number state; in the adjusting process, the positions of the central cone 2 and the splitter plate 3 are continuously adjusted to give consideration to flow distribution and overall performance.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (7)
1. The utility model provides a Ma0-5+ wide region precooling + punching combination engine shaft symmetry adjustable air inlet which characterized in that: the device is composed of a fixed part lip cover (1), a movable part splitter plate (3) and a movable part central cone (2) from outside to inside in a symmetrical mode through a central shaft, wherein the molded surface of the splitter plate (3) is divided into an inner molded surface (4) and an outer molded surface (5), and the splitter plate (3) is located between the lip cover (1) and the central cone (2) all the time under the full working condition; the rear part of the flow distribution plate (3) is a horizontal telescopic section, and the central cone (2) is fixed at the rear part of the flow distribution plate (3) through a telescopic structure;
the central cone (2) and the splitter plate (3) do front and back telescopic translation motion according to flight working condition requirements, the central cone (2) and the inner molded surface (4) of the splitter plate, the lip cover and the outer molded surface (5) respectively form a vortex spraying channel and a sub-combustion stamping channel which are contracted and expanded firstly, and the two channels are always in an open state in the range of Ma0-5 +.
2. The Ma0-5+ Wide Range Pre-Cooling + ramjet combined Engine axisymmetric adjustable intake duct of claim 1, characterized in that, the lip shroud (1) is composed of a tail section with the same width and a front section with gradually decreasing opening;
the front and the back of the flow distribution plate (3) are composed of fan blade sections and horizontal telescopic sections, and the tail end of each horizontal telescopic section is fixed at a support at the tail end of the lip cover (1); the inner molded surface (4) of the fan blade section positioned at the front part of the splitter plate (3) consists of an expansion section, an equidistant section and a contraction section from inside to outside, and the outer molded surface (5) of the fan blade section consists of an inner expansion section and an outer contraction section from inside to outside; the flow distribution plate (3) performs front-back telescopic translational motion through the horizontal telescopic section;
the central cone (2) consists of a middle cylindrical section and a front conical section and a rear conical section, and the rear conical section is fixed between the horizontal telescopic sections of the flow distribution plates (3) through a telescopic structure and is subjected to front and rear telescopic translation movement through the telescopic structure.
3. The Ma0-5+ Wide Range Pre-Cooling + ramjet combined Engine axisymmetric tunable air intake duct of claim 1, characterized in that, when the central cone (2), splitter plate (3) are fully retracted, the front cone section of the central cone (2) is parallel to the contraction section of the inner profile (4) and the cylinder section of the central cone (2) matches with the equidistant section of the inner profile (4); in the advancing process, the minimum flow areas of the turbojet channel and the sub-combustion stamping channel are gradually reduced, and in the process, the horizontal moving distance of the central cone is adjusted according to the incoming flow Mach number to keep shock wave sealing.
4. The Ma0-5+ Wide Range Pre-Cooling + ram Combined Engine axisymmetric adjustable intake duct of claim 1, characterized in that the rear conical section of the horizontal telescopic section of the splitter plate (3) is fixed on the vertical support frame between the horizontal telescopic sections of the splitter plate (3) through a sleeve structure to perform the front and back telescopic translational motion.
5. The Ma0-5+ Wide Range precooling + ramjet combined engine axisymmetric adjustable intake duct of claim 1, characterized in that, with increasing Mach number of incoming flow, the horizontal advance of the central cone (2) ensures high flow coefficient in wide range, achieving shock sealing above Ma2, the horizontal advance of the central cone (2) ensures shock sealing in wide range, intake duct flow coefficient is kept at 1.0; the movable part splitter plate (3) is linked with the central cone (2) and moves forwards horizontally at the same time, so that the contraction ratios of the turbojet channel and the sub-combustion stamping channel are ensured to be increased along with the increase of the Mach number; horizontally moving the movable part splitter plate (3) to adjust the flow distribution of the turbojet channel and the sub-combustion stamping channel; in the gradually-expanding profile of the front section of the lip cover, the maximum windward area of the air inlet channel is increased along the way compared with the capture area.
6. The Ma0-5+ Wide-Range Pre-Cooling + ramjet combined engine axisymmetric adjustable intake duct of claim 1, characterized in that, at low Mach number, the splitter plate (3) is relatively far from the center cone (2), the throat of the turbojet channel is at a rear position, the contraction ratio is small, and the starting performance of the intake duct is satisfied; under the high Mach number, the relative distance between the splitter plate (3) and the central cone (2) is small, the throat of the turbojet channel moves forward, the area is reduced, and the contraction ratio reaches the maximum value.
7. The Ma0-5+ wide-range precooling + ramjet combined engine axisymmetric adjustable inlet duct of claim 1, characterized in that, at low mach numbers, the relative distance between the splitter plate (3) and the lip shroud (1) is large, the throat area is large, the contraction ratio is small, and the ramjet channel is in a normal starting state; under the high Mach number, the relative distance between the splitter plate (3) and the lip cover (1) is reduced, the throat area reaches the minimum value, the contraction ratio is the maximum, and the incoming flow is decelerated to the throat of the sub-combustion stamping channel and then slowly expanded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963940.3A CN110645099B (en) | 2019-10-11 | 2019-10-11 | Ma 0-5+wide-range precooling and stamping combined engine axisymmetric adjustable air inlet passage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963940.3A CN110645099B (en) | 2019-10-11 | 2019-10-11 | Ma 0-5+wide-range precooling and stamping combined engine axisymmetric adjustable air inlet passage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110645099A true CN110645099A (en) | 2020-01-03 |
| CN110645099B CN110645099B (en) | 2024-04-30 |
Family
ID=69012728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910963940.3A Active CN110645099B (en) | 2019-10-11 | 2019-10-11 | Ma 0-5+wide-range precooling and stamping combined engine axisymmetric adjustable air inlet passage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110645099B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610333A (en) * | 2020-12-30 | 2021-04-06 | 南京航空航天大学 | Three-channel axisymmetric adjustable air inlet channel of wide-range combined engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5074118A (en) * | 1989-01-09 | 1991-12-24 | United Technologies Corporation | Air turbo-ramjet engine |
| US5301901A (en) * | 1993-01-29 | 1994-04-12 | General Electric Company | Telescoping centerbody wedge for a supersonic inlet |
| US20120159925A1 (en) * | 2010-12-27 | 2012-06-28 | Duge Robert T | Turbine based combined cycle engine |
| CN107448296A (en) * | 2017-08-07 | 2017-12-08 | 南京航空航天大学 | 07 grades of combined engine air intake ducts of Mach number of pneumatic type/mechanical combination regulation |
| 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 |
| CN109236472A (en) * | 2018-11-27 | 2019-01-18 | 北京航空航天大学 | A kind of axial symmetry change geometry bimodal air intake duct adapting to broad Mach number |
| CN110159434A (en) * | 2018-11-15 | 2019-08-23 | 北京机电工程研究所 | A kind of air intake duct tunable arrangement and method |
| CN211258815U (en) * | 2019-10-11 | 2020-08-14 | 南京航空航天大学 | Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet |
-
2019
- 2019-10-11 CN CN201910963940.3A patent/CN110645099B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5074118A (en) * | 1989-01-09 | 1991-12-24 | United Technologies Corporation | Air turbo-ramjet engine |
| US5301901A (en) * | 1993-01-29 | 1994-04-12 | General Electric Company | Telescoping centerbody wedge for a supersonic inlet |
| US20120159925A1 (en) * | 2010-12-27 | 2012-06-28 | Duge Robert T | Turbine based combined cycle engine |
| CN107448296A (en) * | 2017-08-07 | 2017-12-08 | 南京航空航天大学 | 07 grades of combined engine air intake ducts of Mach number of pneumatic type/mechanical combination regulation |
| 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 |
| CN110159434A (en) * | 2018-11-15 | 2019-08-23 | 北京机电工程研究所 | A kind of air intake duct tunable arrangement and method |
| CN109236472A (en) * | 2018-11-27 | 2019-01-18 | 北京航空航天大学 | A kind of axial symmetry change geometry bimodal air intake duct adapting to broad Mach number |
| CN211258815U (en) * | 2019-10-11 | 2020-08-14 | 南京航空航天大学 | Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610333A (en) * | 2020-12-30 | 2021-04-06 | 南京航空航天大学 | Three-channel axisymmetric adjustable air inlet channel of wide-range combined engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110645099B (en) | 2024-04-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110645100B (en) | Ma0-6+wide-range precooling and stamping combined engine axisymmetric adjustable air inlet passage | |
| CN211258815U (en) | Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet | |
| CN112610333A (en) | Three-channel axisymmetric adjustable air inlet channel of wide-range combined engine | |
| CN104500228B (en) | A kind of structure changes two dimension supersonic speed uptake | |
| US20230010124A1 (en) | Internal-parallel inlet with mode conversion combined with variable geometry adjustment | |
| CN211287901U (en) | Ma0-6+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet | |
| CN102705081A (en) | Binary hypersonic variable geometrical inlet channel, design method and work mode | |
| CN114017198A (en) | Axisymmetric convergent-divergent nozzle | |
| CN114151225B (en) | Throat area adjusting device of dual-channel underpants type spray pipe of engine | |
| US5852928A (en) | Thrust reverser with extendible pivoting baffle | |
| CN105971733B (en) | A kind of closed structure changes Two Dimensional Supersonic air intake duct | |
| CN202628279U (en) | Binary hypersonic speed-variable geometric air inlet channel | |
| CN113374594B (en) | Control mechanism for expansion section of binary spray pipe | |
| CN110645099B (en) | Ma 0-5+wide-range precooling and stamping combined engine axisymmetric adjustable air inlet passage | |
| CN113915027B (en) | Circular-square binary vector spray pipe with yawing function | |
| CN215170392U (en) | Three-channel axisymmetric adjustable air inlet channel of wide-range combined engine | |
| CN112360645A (en) | Tandem turbine/double-mode stamping combined engine mode conversion device | |
| CN212656904U (en) | Shape memory alloy driven variable air inlet driving device | |
| CN114109645A (en) | Axial symmetry contraction and expansion spray pipe movement mechanism | |
| CN115898692A (en) | Combined spray pipe and adjusting method thereof | |
| CN112780441B (en) | Variable flow passage ramjet engine and design and adjustment method | |
| CN111692013A (en) | Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method | |
| CN105351100A (en) | Structural design of inlet isolation segment of rocket-based-combined-cycle engine | |
| CN114753930A (en) | Combined power mode conversion method based on axisymmetric air inlet channel configuration characteristics | |
| CN108087144B (en) | Binary plug type thrust vectoring nozzle and aircraft with same |
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 | ||
| GR01 | Patent grant |