CN111075570A - Geometric adjustable flow passage telescopic compensation and dynamic sealing structure - Google Patents
Geometric adjustable flow passage telescopic compensation and dynamic sealing structure Download PDFInfo
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- CN111075570A CN111075570A CN201911294377.1A CN201911294377A CN111075570A CN 111075570 A CN111075570 A CN 111075570A CN 201911294377 A CN201911294377 A CN 201911294377A CN 111075570 A CN111075570 A CN 111075570A
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- slot
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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
- 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
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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
- F02C7/28—Arrangement of seals
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a geometric adjustable flow passage telescopic compensation and dynamic sealing structure which comprises a fourth adjusting plate and a slot; one end of the fourth adjusting plate is hinged with the third adjusting plate, the other end of the fourth adjusting plate is inserted into the slot and can horizontally stretch out and draw back in the slot, the slot is fixed on the engine, and sealing strips are arranged in gaps between the fourth adjusting plate and the slot to realize dynamic sealing.
Description
Technical Field
The invention belongs to the technical field of pneumatic design of air inlet channels, and particularly relates to a geometric adjustable flow channel telescopic compensation and dynamic sealing structure.
Background
The wide mach number multimode working engine is a research hotspot of the current air suction type engine, wherein the shared adjustable air inlet channel is one of key technologies. At present, a large number of pneumatic design optimization researches of adjustable air inlet channels have been carried out at home and abroad, the scheme of a typical adjustable air inlet channel is shown in figure 1, a cross section of the main structure of the typical adjustable air inlet channel along a symmetrical plane is shown in figure 1, and the air inlet channel is an adjustable air inlet channel with two channels connected in parallel up and down and comprises: the device comprises a side plate 1, a rotatable lip plate 2, a first hinge shaft 3, a high-speed channel top plate 4, a high-speed channel bottom plate 5, a rotatable flow distribution plate 6, a second hinge shaft 7, a low-speed channel top plate 8, a low-speed channel mounting platform 9, a third hinge shaft 10, a first adjusting plate 11, a fourth hinge shaft 12, a second adjusting plate 13, a fifth hinge shaft 14, a third adjusting plate 15, a turbine front mounting interface 16, a turbine engine 17, an adjusting plate adjusting mechanism 18 and a driving device 19. A runner surrounded by the side plate 1, the rotatable lip plate 2, the first hinge shaft 3, the high-speed channel top plate 4, the high-speed channel bottom plate 5, the rotatable flow distribution plate 6 and the second hinge shaft 7 (hidden at the symmetrical sides) is a high-speed channel and is matched with a stamping engine to work. A flow channel surrounded by the side plate 1, the rotatable flow dividing plate 6, the second hinge shaft 7, the low-speed passage top plate 8, the third hinge shaft 10, the first adjusting plate 11, the fourth hinge shaft 12, the second adjusting plate 13, the fifth hinge shaft 14 and the third adjusting plate 15 (hidden at the symmetrical side) is a low-speed passage and is matched with a turbine engine to work.
The adjustable inlet geometry is characterized by two categories: one is a fixed axis rotational movement, such as a rotatable lip plate 2 rotating about a first hinge axis 3 and a rotatable diverter plate 6 rotating about a second hinge axis 7. And secondly, profile lifting combined movement, such as parallel lifting of the second adjusting plate 13 under the restriction of the adjusting plate adjusting mechanism 18. The front end of the first adjusting plate 11 rotates around the third hinge axis 10, the rear end of the first adjusting plate 11 is connected with the front end of the second adjusting plate 13 through a fourth hinge axis 12, and the rear end of the second adjusting plate 13 is connected with the third adjusting plate 15 through a fifth hinge axis 14. Under the driving of the driving device 19, the adjusting plate adjusting mechanism 18 pushes the second adjusting plate 13 to lift, so as to drive the first adjusting plate 11 to rotate in a fixed axis manner and the third adjusting plate 15 to follow. The rotatable splitter plate 6 rotates and moves in combination with the first adjusting plate 11, the second adjusting plate 13 and the third adjusting plate 15 to match the operation of the turbine engine 17. It should be noted that the first adjusting plate 11, the second adjusting plate 13, and the third adjusting plate 15 can realize the adjustment of the throat area of the intake passage in a compound motion manner, and are also suitable for the operation of a ramjet engine.
As can be easily found from FIG. 1, the third adjusting plate 15 and the turbine front mounting interface 16 have a flow discharge channel for discharging partial low-speed channel intake flow, so as to solve the problem of low-speed channel outlet distortion and the problem of inlet shock string control. This brings about two disadvantages: firstly, when the aircraft flight mach number is increased, the air flow entering the air inlet channel low-speed channel can enter the space where the adjusting plate adjusting mechanism 18 and the driving device 19 are located through the leakage channel between the third adjusting plate 15 and the turbine front mounting interface 16, and particularly, the requirement for higher thermal protection is provided for the driving device 19. Secondly, the rear end of the third adjusting plate 15 and the turbine engine 17 have discontinuous profiles, and although low-energy fluid close to the wall surface of the low-speed passage can be discharged through the turbine front mounting interface 16, the exhaust resistance is increased; if exhaust and leakage flow are not carried out, the difficulty of controlling the quality of the inlet flow field of the turbine engine is increased. In addition, if the profile lifting combined motion is applied to a stamping engine, the profile discontinuity at the tail of the third adjusting plate 15 easily causes negative influence on the back pressure resistance of the flow channel along with the increase of the working mach number.
Disclosure of Invention
In view of the above, the present invention provides a geometric adjustable flow passage expansion compensation and dynamic seal structure, which can make the profile between the rear end of the air inlet and the engine continuous, and prevent high temperature gas from entering the equipment compartment of the air inlet.
The technical scheme for realizing the invention is as follows:
a geometric adjustable flow passage telescopic compensation and dynamic sealing structure comprises a fourth adjusting plate and a slot;
one end of the fourth adjusting plate is hinged to the third adjusting plate, the other end of the fourth adjusting plate is inserted into the slot and can horizontally stretch out and draw back in the slot, the slot is fixed on the engine, and sealing strips are arranged in gaps between the fourth adjusting plate and the slot to achieve dynamic sealing.
Further, the slot includes that the slot upper cover plate passes through screw fixed connection with the apron under the slot, slot upper cover plate, and the three lateral wall in the slot all sets up the sealing strip, compresses tightly through apron under slot upper cover plate and the slot, realizes that the fourth regulating plate is on a parallel with the movive direction's two lateral walls move sealedly.
Further, the bottom surface of the fourth regulating plate is provided with a sealing strip mounting groove, a sealing strip is mounted, and dynamic sealing in the height direction of the fourth regulating plate is achieved.
Furthermore, the tail of the fourth adjusting plate is in smooth transition with the front edge of the upper cover plate of the slot, so that the influence of the splicing structure on a flow field of the flow channel is reduced.
Has the advantages that:
the telescopic and dynamic sealing structure provided by the invention realizes the continuity of the adjustable flow passage profile of the engine through structural assembly, and simultaneously increases the installation flexibility of the movable profile and the dynamic sealing strip through the assembly form, is convenient to increase the pre-compression characteristic of the sealing strip, and is beneficial to improving the dynamic sealing effect of the adjustable profile and the capability of resisting the structural deformation of the body.
Drawings
FIG. 1 is a schematic diagram of a conventional adjustable air inlet structure of an engine.
Fig. 2 is a schematic diagram of the principle of the scheme of the invention.
FIGS. 3(a) and (b) are schematic structural diagrams of the present invention.
Fig. 4 is a schematic view of the dynamic seal of the third regulating plate.
FIG. 5 is a schematic view of the bottom dynamic seal of the fourth adjustment plate.
FIG. 6 is a schematic side-view dynamic seal of a fourth modulation plate.
Fig. 7 is a schematic view of the transition between the fourth adjusting plate and the upper cover plate profile of the slot.
Wherein, 1-side plate, 2-rotatable lip plate, 3-first hinge shaft, 4-high speed channel top plate, 5-high speed channel bottom plate, 6-rotatable flow dividing plate, 7-second hinge shaft, 8-low speed channel top plate, 9-low speed channel mounting platform, 10-third hinge shaft, 11-first adjusting plate, 12-fourth hinge shaft, 13-second adjusting plate, 14-fifth hinge shaft, 15-third adjusting plate, 16-turbine front mounting interface, 17-turbine engine, 18-adjusting plate adjusting mechanism, 19-driving device, 20-sixth hinge shaft, 21-fourth adjusting plate, 22-slot, 23-slot upper cover plate, 24-slot lower cover plate, 25-third adjusting plate sealing strip, 26-slot sealing strip, 27-fourth adjusting plate sealing strip and 28-screw.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a geometric adjustable flow passage telescopic compensation and dynamic sealing structure, which firstly adopts the principle shown in figure 2 to solve the problem of flow passage discontinuity between a third adjusting plate 15 and a turbine front mounting interface 16 shown in figure 1, on the basis of the parts shown in figure 1, a hinge is arranged at the rear end of the third adjusting plate 15, a fourth adjusting plate 21 is additionally arranged, and the front ends of the third adjusting plate 15 and the fourth adjusting plate 21 are connected through a sixth hinge shaft 20. The fourth adjusting plate 21 is installed into the slot 22 and can be horizontally extended and contracted in the slot 22. In summary, by adding the sixth hinge shaft 20, the fourth adjusting plate 21 and the slot 22, the flow channel profile continuity problem and the geometric adjustment problem are considered.
Secondly, the present invention focuses on the problem of adjustable flow path dynamic sealing caused by the introduction of the fourth adjusting plate 21 and the inserting slot 22. The structure of the scheme is shown in figure 3. The present invention does not relate to the specific embodiments of the first adjusting plate 11, the fourth hinge shaft 12, the second adjusting plate 13 and the fifth hinge shaft 14, and will not be described in detail herein. The rear end of the third adjusting plate 15 is connected with the fourth adjusting plate 21 through a sixth hinge shaft 20, and a third adjusting plate sealing strip 25 is arranged on the outer side, so that the dynamic sealing problem between the third adjusting plate 15 and the side plate 1 is realized. The slot 22 is divided into a slot upper cover plate 23 and a slot lower cover plate 24, a fourth adjusting plate sealing strip 27 is arranged on the back of the fourth adjusting plate 21, a slot sealing strip 26 is arranged in the slot upper cover plate 23, the slot upper cover plate 23 and the slot lower cover plate 24 are connected through a screw 28, compression of the third adjusting plate sealing strip 25, the slot sealing strip 26 and the fourth adjusting plate sealing strip 27 is achieved, and a dynamic sealing function is achieved.
Finally, the function of the newly added expansion plate solution related to the parts is explained.
The rear end of the third adjusting plate 15 is connected with the fourth adjusting plate 21 through the sixth hinge shaft 20, so that the fixed-shaft rotating motion can be realized, and the dynamic seal in the hinge connection mode has reported other patents, and does not belong to the field of writing of the patent. The third adjusting plate 15 is laterally provided with a dynamic seal mounting groove, and a third adjusting plate sealing strip 25 is mounted for solving the dynamic seal problem between the third adjusting plate 15 and the side plate 1 in the moving process (as shown in fig. 3).
The slot upper cover plate 23 and the slot lower cover plate 24 are connected through a screw 28 to form a slot with equal height and equal width, and a gap exists between the fourth adjusting plate 21 and the slot in height and width, so that the fourth adjusting plate 21 can perform telescopic motion along the slot between the slot upper cover plate 23 and the slot lower cover plate 24. In the process of telescopic movement, a dynamic seal installation groove is arranged below the fourth adjusting plate 21, a fourth adjusting plate sealing strip 27 (shown in fig. 4) is installed and used for blocking high-temperature gas entering the inside of the slot from a gap (in the height direction) between the fourth adjusting plate 21 and the slot, and the high-temperature gas enters a channel of an accessory cavity below the fourth adjusting plate 21 from the bottom of the fourth adjusting plate 21 to realize a dynamic seal function (shown in fig. 5). Be provided with "nearly" style of calligraphy sealing strip between apron 24 under slot upper cover plate 23 and the slot, also be slot sealing strip 26, through the connection of apron 24 under slot upper cover plate 23 and the slot, realize the precompression to slot sealing strip 26, guarantee slot sealing strip 26 and the laminating of fourth regulating plate 21 side direction, be used for the shutoff by the inside high-temperature gas of gap (on the width direction) entering slot between fourth regulating plate 21 and the slot, get into the passageway of fourth regulating plate 21 below annex cavity by fourth regulating plate 21 bottom, realize the dynamic seal function (as shown in fig. 6). Meanwhile, when the fourth adjusting plate 21 and the slot upper cover plate 23 are designed, smooth transition (such as a slope type) is performed on the tail of the fourth adjusting plate 21 and the front edge of the slot upper cover plate 23, so that the influence of the plugging structure on the flow field of the flow channel is reduced (as shown in fig. 7).
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A geometric adjustable flow passage telescopic compensation and dynamic sealing structure is characterized by comprising a fourth adjusting plate and a slot;
one end of the fourth adjusting plate is hinged to the third adjusting plate, the other end of the fourth adjusting plate is inserted into the slot and can horizontally stretch out and draw back in the slot, the slot is fixed on the engine, and sealing strips are arranged in gaps between the fourth adjusting plate and the slot to achieve dynamic sealing.
2. The telescopic compensation and dynamic seal structure for the flow channel with the adjustable geometry as claimed in claim 1, wherein the slot includes an upper slot cover plate and a lower slot cover plate, the upper slot cover plate and the lower slot cover plate are fixedly connected by screws, the three sidewalls in the slot are provided with sealing strips, and the dynamic seal of the two sidewalls of the fourth adjusting plate parallel to the moving direction is realized by the compression of the upper slot cover plate and the lower slot cover plate.
3. The telescopic compensation and dynamic seal structure for the geometrically adjustable flow passage as claimed in claim 1 or 2, wherein the bottom surface of the fourth adjusting plate is provided with a sealing strip mounting groove, and a sealing strip is mounted to realize dynamic seal in the height direction of the fourth adjusting plate.
4. The telescopic compensation and dynamic seal structure for the geometrically adjustable flow channel as claimed in claim 2, wherein the tail of the fourth adjusting plate is in smooth transition with the front edge of the upper cover plate of the slot, so as to reduce the influence of the plugging structure on the flow field of the flow channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911294377.1A CN111075570A (en) | 2019-12-16 | 2019-12-16 | Geometric adjustable flow passage telescopic compensation and dynamic sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911294377.1A CN111075570A (en) | 2019-12-16 | 2019-12-16 | Geometric adjustable flow passage telescopic compensation and dynamic sealing structure |
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| Publication Number | Publication Date |
|---|---|
| CN111075570A true CN111075570A (en) | 2020-04-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911294377.1A Pending CN111075570A (en) | 2019-12-16 | 2019-12-16 | Geometric adjustable flow passage telescopic compensation and dynamic sealing structure |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4539811A (en) * | 1982-01-27 | 1985-09-10 | The United States Of America As Represented By The Secretary Of The Navy | Multi-port dump combustor |
| CN104632411A (en) * | 2015-01-28 | 2015-05-20 | 南京航空航天大学 | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner |
| CN106285946A (en) * | 2016-08-01 | 2017-01-04 | 南京航空航天大学 | The passage of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle |
| CN109472076A (en) * | 2018-10-31 | 2019-03-15 | 北京航空航天大学 | A kind of optimum design method of turbine base combined engine air intake duct mode conversion process moving component corner |
| CN109667670A (en) * | 2019-01-24 | 2019-04-23 | 南京航空航天大学 | A kind of adjustable valve arrangement of whirlpool control that super/hypersonic two dimensional inlet of auxiliary starts |
-
2019
- 2019-12-16 CN CN201911294377.1A patent/CN111075570A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4539811A (en) * | 1982-01-27 | 1985-09-10 | The United States Of America As Represented By The Secretary Of The Navy | Multi-port dump combustor |
| CN104632411A (en) * | 2015-01-28 | 2015-05-20 | 南京航空航天大学 | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner |
| CN106285946A (en) * | 2016-08-01 | 2017-01-04 | 南京航空航天大学 | The passage of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle |
| CN109472076A (en) * | 2018-10-31 | 2019-03-15 | 北京航空航天大学 | A kind of optimum design method of turbine base combined engine air intake duct mode conversion process moving component corner |
| CN109667670A (en) * | 2019-01-24 | 2019-04-23 | 南京航空航天大学 | A kind of adjustable valve arrangement of whirlpool control that super/hypersonic two dimensional inlet of auxiliary starts |
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Application publication date: 20200428 |
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