CN113586287B - Variable combustion chamber throat device for rocket-based combined power cycle engine - Google Patents
Variable combustion chamber throat device for rocket-based combined power cycle engine Download PDFInfo
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- CN113586287B CN113586287B CN202110986727.1A CN202110986727A CN113586287B CN 113586287 B CN113586287 B CN 113586287B CN 202110986727 A CN202110986727 A CN 202110986727A CN 113586287 B CN113586287 B CN 113586287B
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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
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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Abstract
The invention discloses a variable combustion chamber throat device for a rocket-based combined power cycle engine, which comprises: a combustion chamber throat section, a throat block and a driving system; the combustion chamber throat section is a cavity structure enclosed by a shell, and the upper end, the left end inlet end and the right end outlet end of the combustion chamber throat section are both open. The throat block is positioned at an opening at the upper end of the throat section of the combustion chamber, the horizontal plate body covers the opening at the upper end of the throat section of the combustion chamber, and the right end of the horizontal plate body is hinged with the inner side wall of the throat section of the combustion chamber; and the driving system is connected with the top of the horizontal plate body, and applies driving force to the horizontal plate body to drive the horizontal plate body to rotate towards the cavity far away from or close to the throat section of the combustion chamber by taking the hinged end as a fixed end. The throat structure of the combustion chamber of the RBCC engine is changed by adopting a mechanical linkage device, only the angle of the throat block of the combustion chamber rotating up and down needs to be adjusted, the number of the adjusted parts is relatively small, and the required sealing is simpler.
Description
Technical Field
The invention belongs to the technical field of rocket-based combined power cycle combustion chambers, and particularly relates to a throat device of a variable combustion chamber for a rocket-based combined power cycle engine.
Background
The Rocket-Based Combined-Cycle (RBCC) engine is a Combined-Cycle power system which organically combines a Rocket and a dual-mode ramjet engine, utilizes oxygen in the atmosphere to enable sucked air to interact with the working process of the Rocket engine to generate thrust gain, and has the characteristics of reusability, wide-speed-range multi-task work and the like.
If the RBCC engine needs to work efficiently in a wide speed range, the requirement of full trajectory high performance cannot be met by adopting a fixed structure, if in injection and sub-combustion modes, a combustion chamber flow channel generally adopts a convergent-divergent structure to meet the efficient combustion of a combustion chamber, but along with the improvement of the flight Mach number, the heating ratio in the combustion chamber is gradually reduced, the divergent ratio of the combustion chamber needs to be correspondingly reduced so that the combustion chamber has higher engine performance under different flight Mach numbers, and the divergent ratio of the combustion chamber of the RBCC engine with the fixed structure is unchanged. Therefore, the variable structure combustion chamber can solve the problem, and a lot of researches are carried out in China aiming at the variable structure combustion chamber, however, the variable structure scheme adopted at present has more movable parts and has higher requirements on the aspects of sealing, processing, controlling and the like.
Disclosure of Invention
The invention aims to provide a variable combustion chamber throat device for a rocket-based combined power cycle engine, which adopts a mechanical linkage device to change the throat structure of a combustion chamber of an RBCC engine, only needs to adjust the vertical rotating angle of a throat block of the combustion chamber, has relatively fewer adjusting parts and has simpler required sealing.
The invention adopts the following technical scheme: the invention relates to a variable combustion chamber throat device for a rocket-based combined power cycle engine, which comprises: a combustion chamber throat section, a throat block and a driving system; the combustion chamber throat section is a cavity structure enclosed by a shell, and the upper end, the left end inlet end and the right end outlet end of the combustion chamber throat section are both open.
The throat block comprises a horizontal plate body, an arc-shaped vertical plate and two fan-shaped plate bodies; the two fan-shaped plate bodies are vertically arranged at the front end and the rear end of the horizontal plate body, the direction of the fan-shaped plate bodies is consistent with that of the horizontal plate body, and the fan-shaped plate bodies are the same in length; the tips of the two fan-shaped plate bodies are positioned at the right end of the horizontal plate body, the arc-shaped vertical plate is vertically arranged at the left end of the horizontal plate body, and the radian of the left outer side wall of the arc-shaped vertical plate is consistent with that of the cambered surfaces of the two fan-shaped plate bodies;
the throat block is positioned at an opening at the upper end of the throat section of the combustion chamber, the horizontal plate body covers the opening at the upper end of the throat section of the combustion chamber, and the right end of the horizontal plate body is hinged with the inner side wall of the throat section of the combustion chamber;
the driving system is connected with the top of the horizontal plate body, and applies driving force to the horizontal plate body to drive the horizontal plate body to rotate towards the cavity far away from or close to the throat section of the combustion chamber by taking the hinged end as a fixed end; in the rotating process, the horizontal plate body is used as a top plate of the throat section of the combustion chamber, the arc-shaped vertical plate is attached to the left end of the throat section of the combustion chamber, and a cavity with variable size is formed among the horizontal plate body, the arc-shaped vertical plate and the throat section of the combustion chamber.
Further, the driving system comprises an electric cylinder, a bottom plate and a connecting rod; the bottom plate is a plate body and is horizontally arranged above the throat block, and a strip-shaped opening is formed in the plate body along the left and right directions of the plate body;
the connecting rod is obliquely arranged along the left-right direction, the lower end of the connecting rod is connected with the left end of the horizontal plate body, the upper end of the connecting rod is connected with a horizontally arranged supporting slide block, the supporting slide block is connected with a U-shaped supporting seat with an upward opening, the U-shaped supporting seat vertically and upwards penetrates through the long strip-shaped opening, and the U-shaped supporting seat is connected with a push rod of the electric cylinder; the push rod pulls the U-shaped supporting seat to slide left and right along the elongated hole so as to drive the throat block to rotate in the cavity far away from or close to the throat section of the combustion chamber.
Furthermore, a trapezoidal sliding plate is arranged at the bottom of the bottom plate and positioned at the front side and the rear side of the strip-shaped opening respectively, and the side wall of each trapezoidal sliding plate positioned at the side of the strip-shaped opening is an inclined surface inclined towards the front side and the rear side from bottom to top; the front side wall and the rear side wall of the supporting slide block are inclined planes which incline towards the front inner side and the rear inner side from bottom to top, are attached to the side walls of the trapezoidal slide plate and slide left and right along the side walls of the trapezoidal slide plate.
Furthermore, bases 6 are arranged at the left end and the right end of the bottom plate, and the bases 6 are arranged on connecting blocks at the left end and the right end of the throat section of the combustion chamber; each connecting block is arranged at the left end and the right end of the top of the throat section of the combustion chamber, and spans the cavity body forwards and backwards.
Furthermore, a plate body is integrally connected to the right end of the horizontal plate body, the front end and the rear end of the plate body are cylindrical bodies, and hinges are arranged on the cylindrical bodies and hinged to the front inner side wall and the rear inner side wall of the throat section of the combustion chamber.
Furthermore, sealing grooves are formed in the inner walls of the front side plate and the rear side plate of the throat section of the combustion chamber, and the direction of each sealing groove is consistent with the direction of each side plate; lubricating oil cavities consistent with the trend of the lubricating oil cavities are formed in the inner walls of the front side plate and the rear side plate and above the sealing grooves; on the inboard lateral wall of the connecting block of end about, and seted up the seal groove along its trend, on its inboard lateral wall, and be located the top of each seal groove and seted up the lubricating oil pocket rather than trend looks unanimous, each seal groove all is linked together in order, each lubricating oil pocket all is linked together in order.
The invention also discloses an RBCC engine, which comprises the variable combustion chamber throat device for the rocket-based combined power cycle engine, and further comprises a combustion chamber section and a support plate rocket section, wherein the left end of the combustion chamber throat section is sequentially connected with the combustion chamber section and the support plate rocket section in the axial direction.
The invention has the beneficial effects that: 1. the structure of the combustion chamber throat is changed through the rotation of the throat blocking block, so that the area of the combustion chamber throat is changed, and required parts are few. 2. Adopt electronic jar drive connecting rod, the connecting rod drives the throat sprue, realizes the rotation of accurate control combustion chamber throat sprue, and is convenient high-efficient. 3. The throat of the combustion chamber of the RBCC engine can be continuously adjusted in the flying process of 2-7Ma, so that the structure of the combustion chamber of the RBCC engine can be matched with different modes, the combustion chamber is in the optimal working state, and the RBCC engine can stably work in the mode conversion process. 4. The RBCC engine has the capability of efficiently working in a wide speed range.
Drawings
FIG. 1 is a schematic structural view of a variable combustion chamber throat arrangement for a rocket-based combined power cycle engine;
FIG. 2 is a schematic view of the internal structure of a variable combustion chamber throat arrangement for a rocket-based combined power cycle engine;
FIG. 3 is a schematic view of the throat block and drive system of the present invention;
FIG. 4 is a schematic structural view of a part of the components of the drive system of the present invention;
FIG. 5 is a schematic view of a combustion chamber throat cavity seal;
fig. 6 is a schematic view of an RBCC engine incorporating the variable combustion chamber throat arrangement of the present invention.
Wherein: 1. a drive system; 1-1. An electric cylinder; 1-3, a push rod; 2. a connecting rod; 3. a combustion chamber throat section; 5. a base plate; 5-1, forming a strip-shaped hole; 7. connecting blocks; 9. a trapezoidal sliding plate; 11. a throat block; 11-1. Horizontal plate body; 11-2, arc-shaped vertical plates; 11-3, a sector plate body; 12. a connecting member; 13. a hinge; 14. a support plate rocket section; 15. a combustion chamber section; 19. a lubricating oil cavity; 20. a sealing groove; 22. a support slide block; a U-shaped support seat.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a variable combustion chamber throat device for a rocket-based combined power cycle engine, which is shown in figure 1 and comprises: a combustion chamber throat section 3, a throat block 11 and a driving system 1; the combustion chamber throat section 3 is a cavity structure enclosed by a shell, and the upper end, the left end inlet end and the right end outlet end of the combustion chamber throat section are open.
As shown in fig. 2 and 3, the throat block 11 comprises a horizontal plate body 11-1, an arc-shaped vertical plate 11-2 and two sector-shaped plate bodies 11-3; the two fan-shaped plate bodies 11-3 are vertically arranged at the front end and the rear end of the horizontal plate body 11-1, the direction of the fan-shaped plate bodies is consistent with that of the horizontal plate body 11-1, and the fan-shaped plate bodies are the same in length; the tips of the two sector plate bodies 11-3 are positioned at the right end of the horizontal plate body 11-1, the arc-shaped vertical plate 11-2 is vertically arranged at the left end of the horizontal plate body 11-1, and the radian of the left outer side wall of the arc-shaped vertical plate is consistent with the radian of the arc surfaces of the two sector plate bodies 11-3. The throat blocking block 11 is positioned at an upper end opening of the combustion chamber throat section 3, the horizontal plate body 11-1 covers the upper end opening of the combustion chamber throat section 3, and the right end of the horizontal plate body 11-1 is hinged with the inner side wall of the combustion chamber throat section 3.
In order to provide power for the throat block 11, a driving system 1 is arranged and connected with the top of the horizontal plate body 11-1, the driving system applies driving force to the horizontal plate body 11-1 to drive the horizontal plate body 11-1 to rotate in a cavity far away from or close to the throat section 3 of the combustion chamber by taking the hinged end as a fixed end; in the rotating process, the horizontal plate body 11-1 is used as a top plate of the throat section 3 of the combustion chamber, the arc-shaped vertical plate 11-2 is attached to the left end of the throat section 3 of the combustion chamber, and a cavity with variable size is formed among the horizontal plate body 11-1, the arc-shaped vertical plate 11-2 and the throat section 3 of the combustion chamber.
Specifically, the above-described drive system 1 includes an electric cylinder 1-1, a bottom plate 5, and a connecting rod 2; the bottom plate 5 is a plate body and is horizontally arranged above the throat block 11, and a strip-shaped opening 5-1 is formed in the plate body along the left and right directions of the plate body; the connecting rod 2 is obliquely arranged along the left-right direction, the lower end of the connecting rod is connected with the left end of the horizontal plate body 11-1, the upper end of the connecting rod is connected with a horizontally arranged supporting slide block 22, the supporting slide block 22 is connected with a U-shaped supporting seat 23 with an upward opening, the U-shaped supporting seat 23 vertically penetrates through the long strip-shaped opening 5-1,U-shaped supporting seat 23 upwards and is connected with a push rod 1-3 of the electric cylinder 1-1; the push rod 1-3 pulls the U-shaped supporting seat 23 to slide left and right along the elongated opening 5-1 so as to drive the throat block 11 to rotate in the cavity far away from or close to the throat section 3 of the combustion chamber.
As shown in fig. 4, when the supporting slider 22 slides left and right in the elongated opening 5-1, in order to stabilize the supporting slider, the bottom of the bottom plate 2 is closely attached to the wall surface of the bottom plate 2, a trapezoidal sliding plate 9 is respectively arranged at the front side and the rear side of the elongated opening 5-1, and the side wall of each trapezoidal sliding plate 9 at the side of the elongated opening 5-1 is an inclined surface inclined to the front side and the rear side from bottom to top; the front and rear side walls of the supporting slide block 22 are inclined surfaces inclined to the front and rear inner sides from bottom to top, are attached to the side walls of the trapezoidal sliding plate 9, and slide left and right along the side walls of the trapezoidal sliding plate 9.
The bottom plate 5 is horizontally arranged and is placed on the combustion chamber throat section 3, so that bases 6 are arranged at the left end and the right end of the bottom plate 5, the bases 6 are vertical plates which are vertically downward, and the bases 6 are arranged on connecting blocks 7 at the left end and the right end of the combustion chamber throat section 3; each connecting block 7 is arranged at the left end and the right end of the top of the throat section 3 of the combustion chamber, and spans the cavity body forwards and backwards.
The right end of the horizontal plate body 11-1 is integrally connected with a plate body, the front end and the rear end of the plate body are cylindrical bodies, and each cylindrical body is provided with a hinge 13 for being hinged with the front inner side wall and the rear inner side wall of the combustion chamber throat section 3.
As shown in fig. 5, sealing grooves 20 are formed in the inner walls of the front and rear side plates of the combustion chamber throat section 3, and the direction of each sealing groove 20 is consistent with the direction of the side plate; lubricating oil cavities 19 which are consistent with the trend of the sealing grooves 20 are formed in the inner walls of the front side plate and the rear side plate and are positioned above the sealing grooves 20; on the inboard lateral wall of the connecting block 7 of controlling the end, and seted up seal groove 20 along its trend, on its inboard lateral wall, and be located the top of each seal groove and seted up rather than trend unanimous lubricating oil cavity 19. The sealing groove 20 is filled with flexible materials to realize sealing, and a lubricating oil cavity 19 is formed to realize the lubricating effect of the throat block 11 in the moving process. Each seal groove 20 is communicated in sequence, and each lubricating oil cavity 19 is communicated in sequence.
The invention also discloses an RBCC engine, as shown in figure 6, which further comprises a combustion chamber section 15 and a support plate rocket section 14, wherein the left end of the combustion chamber throat section 3 is sequentially connected with the combustion chamber section 15 and the support plate rocket section 14 in the axial direction.
The working process of the variable combustion chamber throat device for the rocket-based combined power cycle engine in the embodiment is as follows: firstly, a push rod 1-3 of an electric cylinder 1-1 drives a connecting rod 2, and translation is converted into up-and-down rotation of a throat block 11 in a certain range through the connecting rod 2, so that the structure of a throat section 3 of a combustion chamber is changed. Along with the gradual increase of the flight Mach number from low to high, the throat sprue 11 rotates towards the cavity of the combustor throat section 3 gradually, so that the area of the combustor throat is reduced gradually, and the size of the combustor throat under different incoming flow conditions is matched. When the combustor works under the condition of the same Mach number, the released heat in the combustor is gradually reduced along with the gradual reduction of the fuel equivalence ratio, and the throat block 11 also rotates towards the cavity of the combustor throat section 3, so that the area of the combustor throat is gradually reduced, and the size of the combustor throat under the condition of different fuel equivalence ratios under the same incoming flow condition is matched.
The variable combustion chamber throat device for the rocket-based combined power cycle engine can meet the requirement of wide inflow range Ma2-7 on the change of the combustion chamber throat.
When the U-shaped supporting seat 23 is positioned at the rightmost end of the elongated opening 5-1, the maximum throat area of the combustion chamber 15 corresponds to the Ma2 incoming flow. When the engines all work at the equivalence ratio of 1, the throat heights of Ma2-7 are respectively 3.0H, 2.4H, 2.0H, 1.6H and 1.2H. When the mach number of the incoming flow is increased to 3, the push rod 1-3 of the electric cylinder 1-1 drives the U-shaped supporting seat 23 to move leftwards, and drives the throat block 11 to rotate towards the cavity of the throat section 3 of the combustion chamber, so that the structure of the throat section 3 of the combustion chamber is changed, and the throat height is changed from 3.0H to 2.5H. Along with the gradual increase of the flight Mach number from low to high, the throat blocking piece 11 continues to rotate in the cavity of the combustor throat section 3, so that the area in the combustor throat section 3 is gradually reduced, the expansion ratio of the combustor under the condition of higher incoming flow is matched, and the device can be respectively adjusted to the area in the combustor throat section 3 corresponding to Ma 2-7. And under the same incoming flow condition, when the fuel equivalence ratio is changed within the range of 1 to 0.6, the throat block 11 of the combustion chamber can be adjusted to be matched with the fuel equivalence ratio, and the mach number is the same as the Mach number of the adjusted matching.
The following experiment was conducted using the RBCC engine of the present invention in which the combustion section 15 was of equal width, the combustion throat section 3 was 3 times the height of the combustion chamber inlet, and H was the combustion chamber inlet height.
When the engine was operated under Ma2, the simulated air flow was 2.8kg/s, total pressure was about 0.3MP, total temperature was 400K, equivalence ratio was 1, and then throat height was 3H. When the equivalence ratio is reduced from 1 to 0.6, the throat height is reduced from 3H to 2.5H, and the throat block 11 rotates towards the throat section 3 of the combustion chamber by an angle from 0 degree to 5 degrees.
When the engine was operated at Ma3, the simulated air flow was 4.7kg/s, total pressure was about 0.6MP, total temperature 606K, equivalence ratio was 1, and throat height was 2.5H. When the equivalence ratio is reduced from 1 to 0.6, the throat height is reduced from 2.4H to 2.0H, and the rotation angle of the throat block 11 towards the throat section 3 of the combustion chamber is from 6 degrees to 10 degrees.
When the engine was operated at Ma4, the simulated air flow was 4.0kg/s, total pressure was about 0.9MP, total temperature was 900K, equivalence ratio was 1, and then throat height was 2.0H. When the equivalence ratio is reduced from 1 to 0.6, the throat height is reduced from 2.0H to 1.6H, and the rotation angle of the throat block 11 to the throat section 3 of the combustion chamber is from 10 degrees to 14 degrees.
When the engine was operated at Ma5, the simulated air flow was 3.6kg/s, total pressure was about 1.2MP, total temperature 1300K, equivalence ratio 1, and throat height was 1.6H. When the equivalence ratio is reduced from 1 to 0.6, the throat height is reduced from 1.6H to 1.4H, and the rotation angle of the throat block 11 to the combustion chamber throat section 3 is from 14 degrees to 16 degrees.
When the engine was operated with Ma6-7 flow, the simulated air flow was 3.3kg/s, the total pressure was about 1.4MP, the total temperature was 1650K, the equivalence ratio was 1, and the throat height was 1.4H. When the equivalence ratio is reduced from 1 to 0.6, the throat height is reduced from 1.2H to 1.0H, and the rotation angle of the throat block 11 to the throat section 3 of the combustion chamber is from 16 degrees to 20 degrees.
Claims (6)
1. A variable combustion chamber throat arrangement for a rocket-based combined power cycle engine, comprising: a combustion chamber throat section (3), a throat block (11) and a driving system (1);
the combustion chamber throat section (3) is of a cavity structure enclosed by a shell, and the upper end, the left end inlet end and the right end outlet end of the combustion chamber throat section are both open;
the throat block (11) comprises a horizontal plate body (11-1), an arc-shaped vertical plate (11-2) and two fan-shaped plate bodies (11-3); the two fan-shaped plate bodies (11-3) are vertically arranged at the front end and the rear end of the horizontal plate body (11-1), the trend of the fan-shaped plate bodies is consistent with that of the horizontal plate body (11-1), and the fan-shaped plate bodies are the same in length; the tips of the two fan-shaped plate bodies (11-3) are positioned at the right end of the horizontal plate body (11-1), the arc-shaped vertical plate (11-2) is vertically arranged at the left end of the horizontal plate body (11-1), and the radian of the left outer side wall of the arc-shaped vertical plate is consistent with the radian of the arc surfaces of the two fan-shaped plate bodies (11-3);
the throat block (11) is positioned at an opening at the upper end of the combustion chamber throat section (3), the horizontal plate body (11-1) covers the opening at the upper end of the combustion chamber throat section (3), the right end of the horizontal plate body (11-1) is hinged with the inner side wall of the combustion chamber throat section (3),
the driving system (1) is connected with the top of the horizontal plate body (11-1) and applies driving force to the horizontal plate body (11-1) to drive the horizontal plate body (11-1) to rotate towards a cavity far away from or close to the combustion chamber throat section (3) by taking the hinged end as a fixed end; in the rotating process, the horizontal plate body (11-1) is used as a top plate of the combustion chamber throat section (3), the arc-shaped vertical plate (11-2) is attached to the left end of the combustion chamber throat section (3), and a cavity with variable size is formed among the horizontal plate body (11-1), the arc-shaped vertical plate (11-2) and the combustion chamber throat section (3);
the driving system (1) comprises an electric cylinder (1-1), a bottom plate (5) and a connecting rod (2);
the bottom plate (5) is a plate body and is horizontally arranged above the throat block (11), and a strip-shaped opening (5-1) is formed in the plate body along the left and right directions of the plate body;
the connecting rod (2) is obliquely arranged along the left-right direction, the lower end of the connecting rod is connected with the left end of the horizontal plate body (11-1), the upper end of the connecting rod is connected with a horizontally arranged supporting slide block (22), the supporting slide block (22) is connected with a U-shaped supporting seat (23) with an upward opening, the U-shaped supporting seat (23) vertically and upwardly penetrates through the elongated open hole (5-1), and the U-shaped supporting seat (23) is connected with a push rod (1-3) of the electric cylinder (1-1); the push rod (1-3) pulls the U-shaped supporting seat (23) to slide left and right along the long strip-shaped opening (5-1) so as to drive the throat plugging block (11) to rotate in the cavity far away from or close to the combustion chamber throat section (3).
2. The variable combustion chamber throat device for the rocket-based combined power cycle engine according to claim 1, wherein a trapezoidal sliding plate (9) is respectively arranged at the bottom of the bottom plate (5) and at the front side and the rear side of the strip-shaped opening (5-1), and the side wall of each trapezoidal sliding plate (9) at the side of the strip-shaped opening (5-1) is an inclined surface which inclines to the front side and the rear side from bottom to top; the front side wall and the rear side wall of the supporting sliding block (22) are inclined planes which incline towards the front inner side and the rear inner side from bottom to top, are attached to the side wall of the trapezoidal sliding plate (9), and slide left and right along the side wall of the trapezoidal sliding plate (9).
3. The variable combustion chamber throat device for a rocket-based combined power cycle engine according to claim 2, wherein bases (6) are arranged at both left and right ends of the bottom plate (5), the bases (6) are arranged on connecting blocks (7) at left and right ends of the combustion chamber throat section (3); each connecting block (7) is arranged at the left end and the right end of the top of the combustion chamber throat section (3) and spans the cavity front and back.
4. A variable combustion chamber throat device for a rocket-based combined power cycle engine according to claim 3, wherein a plate is integrally connected to the right end of the horizontal plate (11-1), and the front and rear ends of the plate are cylindrical bodies, each of which is provided with a hinge (13) for hinging with the front and rear inner side walls of the combustion chamber throat section (3).
5. The variable combustion chamber throat device for the rocket-based combined power cycle engine according to claim 4, wherein the inner walls of the front and rear side plates of the combustion chamber throat section (3) are provided with sealing grooves (20), and the direction of each sealing groove (20) is consistent with the direction of the side plates; lubricating oil cavities (19) with the same trend as the sealing grooves (20) are formed in the inner walls of the front side plate and the rear side plate and above the sealing grooves; sealing grooves (20) are formed in the inner side walls of the left end and the right end of the connecting block (7) along the direction of the connecting block, and lubricating oil cavities (19) consistent with the direction of the sealing grooves are formed in the inner side walls of the connecting block and above the sealing grooves; the sealing grooves (20) are communicated in sequence, and the lubricating oil cavities (19) are communicated in sequence.
6. An RBCC engine, comprising a variable combustion chamber throat arrangement for a rocket-based combined power cycle engine as claimed in any one of claims 1-5, further comprising a combustion chamber section (15) and a rocket plate section (14), the left end of said combustion chamber throat section (3) being axially connected in series with the combustion chamber section (15) and the rocket plate section (14).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110986727.1A CN113586287B (en) | 2021-08-26 | 2021-08-26 | Variable combustion chamber throat device for rocket-based combined power cycle engine |
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| CN202110986727.1A CN113586287B (en) | 2021-08-26 | 2021-08-26 | Variable combustion chamber throat device for rocket-based combined power cycle engine |
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| CN113586287B true CN113586287B (en) | 2022-10-14 |
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| US7793504B2 (en) * | 2006-05-04 | 2010-09-14 | Rolls-Royce Corporation | Nozzle with an adjustable throat |
| FR2957385B1 (en) * | 2010-03-12 | 2012-07-06 | Snecma Propulsion Solide | TUYERE WITH ORIENTABLE COLLAR |
| CN201954030U (en) * | 2011-02-09 | 2011-08-31 | 娄底市佳华机械有限公司 | Upper swinging type fan-shaped gate |
| RU2472956C2 (en) * | 2011-04-29 | 2013-01-20 | Открытое акционерное общество "ОКБ Сухого" | Supersonic controlled air intake |
| CN105240160B (en) * | 2015-10-29 | 2017-06-09 | 西北工业大学 | A kind of rocket based combined cycle engine structure changes combustion chamber |
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