CN116537944A - Variable geometry structure of internal parallel type air inlet diffuser - Google Patents
Variable geometry structure of internal parallel type air inlet diffuser Download PDFInfo
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- CN116537944A CN116537944A CN202310236874.6A CN202310236874A CN116537944A CN 116537944 A CN116537944 A CN 116537944A CN 202310236874 A CN202310236874 A CN 202310236874A CN 116537944 A CN116537944 A CN 116537944A
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- plate
- channel
- air inlet
- rotary
- power source
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- 230000006835 compression Effects 0.000 claims abstract description 9
- 238000007906 compression Methods 0.000 claims abstract description 9
- 239000012530 fluid Substances 0.000 claims abstract description 7
- 238000009792 diffusion process Methods 0.000 claims abstract description 6
- 238000004080 punching Methods 0.000 claims description 24
- 230000009021 linear effect Effects 0.000 claims description 15
- 230000007246 mechanism Effects 0.000 claims description 11
- 230000009471 action Effects 0.000 claims description 5
- 238000010248 power generation Methods 0.000 claims 1
- 230000003584 silencer Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 25
- 230000008569 process Effects 0.000 abstract description 23
- 238000006243 chemical reaction Methods 0.000 abstract description 16
- 230000008859 change Effects 0.000 description 6
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000002243 precursor Substances 0.000 description 3
- 230000001105 regulatory effect Effects 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a variable geometry structure of an internal parallel type air inlet passage diffusion section, which comprises an external compression section and an internal compression section at the front part of an air inlet passage, a throat plate with adjustable height at the middle part of the air inlet passage and a variable geometry diffusion section at the rear part of the air inlet passage. The throat height is actively adjusted according to the Mach number of the incoming flow; the turbine channel and the stamping channel are controlled to be switched through rotation of the splitter plate, so that the working states of the two air inlets are switched, the fluid control in the air inlets is realized through controlling the variable geometry structure of the lower half section of the diffuser section, when the position of the splitter plate is fixed, the flow redistribution in the two channels is realized through the variable geometry structure adjustment of the lower end of the diffuser section, the requirements of an engine on incoming flow quality and flow in the mode conversion process are met, and the flow field stability of the air inlets in the mode conversion process is realized. The power source with the structure can be integrated with the power source at the throat, and the requirements can be met by improving the power source on the basis of the original internal parallel exhaust passage.
Description
Technical Field
The invention belongs to the technical field of combined air inlet channel mode conversion methods, and particularly relates to a variable geometry air inlet channel structure design used in an internal parallel TBCC propulsion system mode conversion process.
Background
With the increasing performance demands of aircraft, providing suitable airflow to engines to provide aircraft with a wider operating mach range and operational reliability is also necessarily a new development direction, and thus the development of air inlets is very important. The intake duct needs to provide the engine with a proper air flow to meet the requirements of the combustion chamber, especially in the mode conversion process, and the intake duct needs to provide the air flow to the two engines, so the design of the intake duct is necessary.
The mode conversion process refers to the process of switching between the operation of the turbine engine at the low Mach number and the operation of the ramjet engine at the high Mach number, and whether proper flow and an internal flow field of the air inlet channel can be provided for the two engines in the mode conversion process is stable or not is related to whether the mode conversion process can be stably transited or not.
In summary, aiming at the pneumatic coupling phenomenon between two air inlets in the air inlet modal transformation process, how to slow down the influence of the phenomenon on the air flow is one of the technical difficulties of modal switching, so it is necessary to study the variable geometry structure matched with the modal transformation of the TBCC air inlet.
Disclosure of Invention
The invention aims to provide an internal parallel connection type air inlet diffuser variable geometry structure, wherein the air inlet diffuser can be adjusted according to the back pressure of outlets of two air inlets in the mode conversion process, so that a stable flow field of an internal parallel connection TBCC air inlet in the mode conversion process can be realized; the flow distribution of the two channels in the mode conversion process is regulated, so that the flow requirement of the turbine engine and the ramjet engine during working is met.
The technical solution for realizing the purpose of the invention is as follows:
an inner parallel type air inlet diffuser variable geometry structure is provided with a lip cover, an outer compression inclined plate, a throat plate and a splitter plate in sequence in an air inlet;
the lip cover is fixedly arranged in the air inlet channel, the throat plate is hinged with the rotary arc plate, and the flow dividing plate is hinged at the wall surface between the rear turbine channel and the stamping channel; the rotary arc plate and the rotary diffusion plate realize oblique movement of the lower wall surface through a lower hinge point, so as to adjust the area ratio of the punching channel to the turbine channel;
when fluid in the punching passage overflows from the flow dividing plate into the turbine passage, the rotary arc plate and the rotary diffusion plate move obliquely upwards, so that the area ratio of the punching passage to the turbine passage is improved, and the back pressure resistance of the punching passage is improved; when the fluid in the turbine channel overflows from the splitter plate to the punching channel, the rotary circular arc plate and the rotary diffuser plate move obliquely downwards, so that the area ratio of the turbine channel to the punching channel is improved, and the back pressure resistance of the turbine channel is improved.
Compared with the prior art, the invention has the remarkable advantages that:
(1) According to the variable geometry structure of the internal parallel connection type air inlet diffuser, the area ratio of the turbine channel circulation to the punching channel in the mode change process is changed by adjusting the rotary arc plate and the rotary diffuser plate of the air inlet, so that the stable control of the flow field in the air inlet in the mode conversion process is realized, the redistribution of the flow of the turbine and the punching channel is realized, the requirements of a turbine engine and a punching engine on the incoming flow quality are met, and the back pressure resistance of the two channels is improved.
(2) Through using single power supply, only need improve on original intake duct, control two actuating levers through two crank link mechanism, realize the control to the mode in-process intake duct, spare part is few, makes the improvement convenience.
Drawings
FIG. 1 is a schematic illustration of a variable geometry internal parallel inlet diffuser according to the present invention;
FIG. 2 is a schematic illustration of the variation of the rotational arc plate and rotational diffuser of an internal parallel inlet diffuser geometry of the present invention with the splitter plate at the upper end;
FIG. 3 is a schematic diagram of a variation in geometry between a rotating circular arc plate and a rotating diffuser plate of an internal parallel inlet diffuser of the present invention when the splitter plate is at the lower end.
FIG. 4 is a perspective view of a variable geometry block diagram of an internal parallel inlet diffuser according to the present invention.
Fig. 5 is a graph showing the variation of the flow coefficient of the inlet channel and the flow coefficient of the punched channel in the conversion process in the present embodiment.
In the figure, the engine comprises a lip cover 1, a precursor inclined plate 2-1, an external compression inclined plate 2-2, an inclined line actuating rod 3, a throat plate 4, a rotary arc plate 5, a rotary expansion plate 6, a flow dividing plate 7, a linear actuating rod 8 and a combined power source 9.
Description of the embodiments
The invention is further described with reference to the drawings and specific embodiments.
The invention discloses a variable geometry structure of an internal parallel type air inlet diffuser, which is shown in figure 1 and comprises a lip cover 1, a precursor inclined plate 2-1, an external compression inclined plate 2-2, an oblique line action rod 3, a throat plate 4, a rotary arc plate 5, a rotary diffuser plate 6, a splitter plate 7, a linear action rod 8 and a combined power source 9. The outer compression inclined plate 2-2 is hinged with the throat plate 4, and the outer compression inclined plate 2-2 and the throat plate 4 are driven to synchronously rotate by the adjusting mechanism, so that the throat height is adjusted to meet the purposes of various states. The throat plate 4 is hinged with the rotary arc plate 5. The front half part consists of a precursor sloping plate 2-1, an external compression sloping plate 2-2, a throat plate 4 and a linear actuating rod 8. The mode change process refers to a process in which the front end of the flow dividing plate 7 is turned from the upper wall surface to the lower wall surface and from the lower wall surface to the upper wall surface. The movable arc plate 5 and the rotary pressure expansion plate 6 realize the oblique movement of the lower wall surface through a lower hinge point so as to meet the flow distribution in the two air inlets in the modal change process and ensure the stability of the flow field.
The adjusting mechanism comprises a combined power source 9, a linear actuating rod 8, an oblique line actuating rod 3, a throat plate 4, a rotary arc plate 5 and a rotary pressure expansion plate 6, wherein the linear actuating rod (8) is vertically arranged, and a hinge point between the oblique line actuating rod (3) and the rotary arc plate 5 as well as between the oblique line actuating rod and the rotary pressure expansion plate 6 is arranged in a herringbone shape. The combined power source 9 is arranged in the air inlet channel, the linear actuating rod 8 and the oblique line actuating rod 3 are connected to the combined power source 9 through a crank sliding block mechanism, and the rotary motion output by a motor of the combined power source 9 is converted into linear reciprocating motion of the linear actuating rod and oblique line reciprocating motion of the oblique line actuating rod, so that the area ratio of the two air inlet channels in the throat height and the modal change process is controlled, the flow distribution in the two air inlet channels in the modal change process is met, and the stability of a flow field is ensured.
The working principle of the invention is as follows: the mode change process of the air inlet channel is usually under a certain flight state, the position of the front half part is not changed, the mode conversion scheme is only described in the embodiment, the adjustment of the front half part is not specifically described, and the front half part is not adjusted in the mode conversion process. At this time, the splitter plate starts to rotate at a certain rotation speed, the two air inlets work simultaneously, when the back pressure of the punching channel outlet (upper side in the figure) and the turbine channel outlet (lower side in the figure) increases to a certain extent, the flow field in the air inlets is disturbed, the phenomenon of overflow in the pipe can occur between the two channels at the front end of the splitter plate, at this time, the throat height is unchanged, the linear actuating rod 8 and the throat plate 4 are kept unchanged, the motor of the combined power source 9 drives the oblique line actuating rod 3 through the crank sliding block mechanism, so that the rotary arc plate 5 and the rotary pressure expanding plate 6 shrink or expand in an oblique direction,
as shown in FIG. 2, when the splitter plate is at a certain fixed position at the upper end, the excessive back pressure of the outlet of the punching air inlet channel can cause the phenomenon of air flow disturbance in the air inlet channel, at the moment, the front end of the splitter plate needs to be improved, the oblique line action rod starts to move obliquely upwards, the rotating arc plate and the rotating diffuser plate are driven to move obliquely upwards, the area of the turbine channel is reduced, the area ratio of the punching channel to the turbine channel is improved, and the total capture flow of the air inlet channel is not changed, so that the flow of the punching channel is increased and the flow of the turbine channel is reduced by adjusting the flow.
In order to increase the flow in the turbine channel and ensure the stability of the flow field in the air inlet channel, the regulating mechanism is shown in fig. 3, the flow dividing plate is at a certain fixed position at the lower end, the oblique line action rod starts to move obliquely downwards, the rotating circular arc plate and the rotating diffusion plate are driven to move obliquely downwards, the area ratio of the turbine channel to the punching channel is increased, and the total capture flow of the air inlet channel is not changed, so that the flow of the turbine channel is increased and the flow of the punching channel is reduced by regulating the flow.
Specifically, fig. 5 shows the flow coefficient of the air inlet channel in the conversion process of fig. 2, the flow coefficient of the punching channel is changed in this embodiment, the abscissa "p" represents the ratio of the outlet back pressure of the punching channel to the static pressure of the incoming flow, and the ordinate is the flow coefficient of the outlet of the air inlet channel. The outlet pressure of the stamping channel before the variable geometry structure exceeds 12 times of incoming flow pressure, and the outlet pressure of the stamping channel after the variable geometry structure exceeds 14 times of incoming flow pressure, so that the back pressure resistance of the stamping channel before and after the structure is changed can be seen to be improved from 12 times of incoming flow static pressure to 14 times of incoming flow static pressure, and the overflow phenomenon in the pipe is delayed.
When the upper air inlet channel is opened to start the ramjet engine to start running and the position of the splitter plate is fixed, when the combustion in the ram combustion chamber is too severe, the back pressure of the outlet of the ram air inlet channel is too large, fluid in the ram air channel overflows from the splitter plate 7 into the turbine air inlet channel, the rotary arc plate 5 and the rotary pressure expansion plate 6 move obliquely upwards, the area ratio of the ram air channel to the turbine air channel can be improved, the back pressure resistance of the ram air inlet channel is improved, and overflow is restrained. When the turbine engine is started to start running by the lower air inlet channel, when the back pressure of the outlet of the turbine channel is overlarge, fluid in the air inlet channel overflows from the air inlet channel inlet through the flow dividing plate 7, the rotating arc plate 5 and the rotating pressure expanding plate 6 move obliquely downwards, the area ratio of the turbine channel to the punching channel is increased, the back pressure resistance of the turbine air inlet channel is improved, and overflow is restrained.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. An inner parallel connection type air inlet diffusion section variable geometry structure is characterized in that a lip cover (1), an outer compression inclined plate (2-2), a throat plate (4) and a flow dividing plate (7) are sequentially arranged in an air inlet;
the lip cover (1) is fixedly arranged in the air inlet channel, the throat plate (4) is hinged with the rotary arc plate (5), and the flow dividing plate (7) is hinged at the wall surface between the rear turbine channel and the stamping channel; the rotary arc plate (5) and the rotary pressure expansion plate (6) realize the oblique movement of the lower wall surface through a lower hinge point, so as to adjust the area ratio of the punching channel to the turbine channel;
when fluid in the punching channel overflows from the flow dividing plate (7) into the turbine channel, the rotary arc plate (5) and the rotary pressure expanding plate (6) move obliquely upwards, so that the area ratio of the punching channel to the turbine channel is improved, and the back pressure resistance of the punching channel is improved; when fluid in the turbine channel overflows from the flow dividing plate (7) into the punching channel, the rotary arc plate (5) and the rotary pressure expanding plate (6) move obliquely downwards, so that the area ratio of the turbine channel to the punching channel is improved, and the back pressure resistance of the turbine channel is improved.
2. The variable geometry structure of an internal parallel type air inlet diffuser according to claim 1, wherein the rotary arc plate (5) and the rotary diffuser plate (6) realize oblique movement through an adjusting mechanism; the adjusting mechanism comprises a combined power source (9) and a diagonal action rod (3), wherein the combined power source (9) is arranged at the lower end of the air inlet channel, and the diagonal action rod (3) is connected to the combined power source (9) and makes diagonal reciprocating motion under the driving of the combined power source (9).
3. The variable geometry structure of an internal parallel connection type air inlet diffuser according to claim 2, wherein the adjusting mechanism further comprises a linear actuating rod (8), and the linear actuating rod (8) is connected to the combined power source (9) and is driven by the combined power source (9) to do linear reciprocating motion for driving the throat plate (4) to move.
4. An internal parallel inlet diffuser variable geometry according to claim 3, characterized in that the linear actuating rod (8) is arranged vertically.
5. An internal parallel connection type air inlet diffuser variable geometry structure according to claim 2, wherein the hinge point between the oblique line actuating rod (3) and the rotary arc plate and the rotary diffuser plate is arranged in a herringbone shape.
6. The exhaust power generation type impeller silencer for the automobile according to claim 2, wherein the built-in motor of the combined power source (9) converts the output rotary motion of the motor into the linear reciprocating motion of the linear actuating rod (8) through a crank-link mechanism, and the built-in motor of the combined power source (9) converts the output rotary motion of the motor into the oblique reciprocating motion of the oblique actuating rod (3) through the crank-link mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310236874.6A CN116537944A (en) | 2023-03-13 | 2023-03-13 | Variable geometry structure of internal parallel type air inlet diffuser |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310236874.6A CN116537944A (en) | 2023-03-13 | 2023-03-13 | Variable geometry structure of internal parallel type air inlet diffuser |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116537944A true CN116537944A (en) | 2023-08-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310236874.6A Pending CN116537944A (en) | 2023-03-13 | 2023-03-13 | Variable geometry structure of internal parallel type air inlet diffuser |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116537944A (en) |
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2023
- 2023-03-13 CN CN202310236874.6A patent/CN116537944A/en active Pending
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