CN113137634A - Variable-structure bimodal stamping combustion chamber - Google Patents
Variable-structure bimodal stamping combustion chamber Download PDFInfo
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- CN113137634A CN113137634A CN202110614654.3A CN202110614654A CN113137634A CN 113137634 A CN113137634 A CN 113137634A CN 202110614654 A CN202110614654 A CN 202110614654A CN 113137634 A CN113137634 A CN 113137634A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
Abstract
A variable-structure bimodal stamping combustion chamber relates to an aircraft engine combustion chamber. The device comprises an isolation section, a concave cavity, a sudden expansion section, an adjustable deformation section, a pioneer hydrogen injection module, a kerosene injection module, a connecting rod and a hydraulic drive; the profile of the combustion chamber is adjusted through the driving of the hydraulic connecting rod, so that the combustion chamber can work in different modes under different flight Mach numbers. When the Ma is more than 2 and less than 4, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block to adjust the molded surface of the combustion chamber into an equal straight section and a gradually expanding section, and the tail nozzle is a Laval nozzle; when Ma is more than or equal to 4 and less than 6, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block to adjust the molded surface of the combustion chamber into an equal straight section, a diffusion section and an equal straight section; when Ma is more than or equal to 6.0, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block to adjust the molded surface of the combustion chamber into an equal straight section, a diffusion section and a pure expansion nozzle. The working performance of the combustion chamber under the wide Mach number is improved, the heat efficiency and the fuel specific impulse are improved, the boost oil consumption is reduced, and the flight range is improved.
Description
Technical Field
The invention relates to an aeroengine combustion chamber, in particular to a variable-structure bimodal stamping combustion chamber with an adjustable combustion chamber profile.
Background
The performance of the Ramjet is optimal when the flight mach number Ma >3, with sub-Combustion ramjets performing better than scramjets when the flight mach number Ma is between 3 and 6, and with scramjets performing better than sub-Combustion ramjets when the flight mach number Ma >6 (Weber R J, Mackay J s.an Analysis of Ramjet Engines using super-Combustion [ R ]. NASA TN 4386, 1958). In order to obtain optimum performance, the ramjet engine must be operated in a bi-modal manner. During the acceleration of the hypersonic aircraft with the double-mode ramjet engine as the propulsion device, the heat release quantity and the distribution in the combustion chamber must be correspondingly adjusted, so that the engine is converted from a sub-combustion mode to a hyper-combustion mode. During the mode conversion, the wall pressure distribution changes significantly as the combustion chamber boundary conditions suddenly change from a thermally choked state to a non-choked state. This causes sudden changes in thrust and momentum acting on the aircraft, which may result in the aircraft losing control. Therefore, how to realize smooth conversion of different combustion modes is a technical difficulty in the design of the combustion chamber.
The variable-structure dual-mode stamping combustion chamber can concentrate the sub-combustion mode and the scram mode on the same engine by reasonably controlling a combustion chamber runner and a fuel injection mode and utilizing a thermal choking method. In addition to fuel injection control, the operating mode of the combustion chamber can be varied by profile adjustment as compared to conventional dual-mode ramjet combustors. The profile of the combustion chamber is adjusted to be a gradually expanding combustion chamber in a sub-combustion mode, the tail nozzle is a Laval nozzle which forms thermal choke while the over-combustion mode is adjusted to be a pure expansion nozzle which enables the combustion chamber to be in a stable transition from a thermal choke state to a non-choke state. The variable-structure bimodal stamping combustion chamber has better performance at each flight Mach number through profile adjustment, and has good development prospect.
Disclosure of Invention
The invention aims to provide a variable-structure bimodal ramjet combustion chamber which can adjust the profile of the combustion chamber, effectively improve the working performance of the combustion chamber of a bimodal ramjet engine under a wide Mach number, improve the working reliability of the bimodal ramjet engine under a low Mach number, and avoid the installation of an accelerating power device with a low Mach number, thereby greatly reducing the weight and the windward area of an aircraft. The connecting rod and the hydraulic drive are arranged on the outer wall surface of the combustion chamber, the profile of the combustion chamber is changed by swinging the connecting rod, so that the combustion chamber has better performance, the heat efficiency and the fuel specific impulse are improved, the oil consumption is reduced, the flight range is improved, and the working Mach number range of the combustion chamber is expanded.
The variable-structure bimodal stamping combustion chamber comprises an isolation section, a concave cavity, a sudden expansion section, an adjustable variable section, a pioneer hydrogen injection module, a kerosene injection module, a connecting rod and a hydraulic connecting rod drive;
the isolation section, the sudden expansion section and the adjustable deformation section are sequentially connected, and the isolation section and the sudden expansion section form a fixed section; the pioneer hydrogen module and the kerosene injection module are fixed on the sudden expansion section and are used for injecting hydrogen and kerosene; the concave cavity is arranged on the lower wall surface of the combustion chamber, and the bottom of the concave cavity is provided with a spark plug for ignition; the hydraulic connecting rod drives the adjustable variable section to act through the connecting rod, and the profile of the combustion chamber is adjusted through the hydraulic connecting rod driving, so that the combustion chamber works in different modes under different flight Mach numbers.
The sudden expansion section and the concave cavity are used for maintaining the stable flame tissue to be combusted and then are discharged from the adjustable nozzle formed by the adjustable deformation section to generate thrust.
The isolation section and the sudden expansion section are connected through a bolt.
The pioneer hydrogen injection module and the kerosene injection module can be fixed on the fixed section through bolts.
The adjustable variable section and the fixed section are fixedly connected through a flange plate.
The adjustable deformation sections comprise a first adjustable deformation section, a second adjustable deformation section and a third adjustable deformation section, and the adjustable deformation sections are fixedly connected through connecting flanges; the first hydraulic drive and the first connecting rod are connected with the first adjustable variable section through a first connecting block; and the second hydraulic drive and the second connecting rod are connected with the third adjustable variable section through a second connecting block.
The combustion chamber works in different modes under different flight Mach numbers, including a sub-combustion mode, a mixed mode and a super-combustion mode;
in the sub-combustion mode, when the Mach number is more than 2.0 and less than 4.0, the adjustable variable section position is changed through the connecting rod and the connecting block by hydraulic drive, so that the molded surface of the combustion chamber is adjusted to be an equal straight section and a gradually expanding section, and the tail nozzle is a Laval nozzle;
in a mixed mode, when the Mach number is more than or equal to 4.0 and less than 6.0, the position of the adjustable variable section is changed through the connecting rod and the connecting block by hydraulic drive, so that the molded surface of the combustion chamber is adjusted to be an equal straight section, a diffusion section and an equal straight section;
in the scramjet mode, when the Mach number is more than or equal to 6.0, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block, so that the molded surface of the combustion chamber is adjusted to be an equal straight section, a diffusion section and a pure expansion nozzle.
The invention provides the working principle and the steps of the invention:
1. the device is provided with an isolation section, a concave cavity, a sudden expansion section, an adjustable deformation section, a fixed section, a pioneer hydrogen injection module, a kerosene injection module, a connecting rod and a hydraulic connecting rod drive;
2. incoming flow air enters through an inlet of the isolation section, hydrogen and kerosene are respectively sprayed through a pioneer hydrogen module and a kerosene spraying module at the upstream of the combustion chamber, and the spraying of the hydrogen is stopped after the ignition is successful;
3. the incoming flow air and part of kerosene are mixed and then enter the sudden expansion section, part of un-mixed kerosene and incoming flow enter the concave cavity at the lower part for further mixing, and part of un-mixed kerosene and incoming flow enter the step sudden expansion area at the upper part for further mixing. The spark plug at the bottom of the cavity realizes the active ignition of the gas and the cavity plays a role in flame stabilization. Along with the diffusion of the flame, high-temperature gas generated by combustion is discharged through the spray pipe so as to generate thrust;
4. along with the change of the flight Mach number, the variable-structure bimodal stamping combustion chamber works in different modes: in a sub-combustion mode (2< Ma <4), the combustion chamber is driven by a hydraulic connecting rod to be an equal straight section and a gradually-expanded profile, so that the total pressure loss is reduced, and the tail nozzle is adjusted to be a Laval nozzle so as to control thermal choke. The back pressure caused by fuel combustion can cause the boundary layer at the inlet of the combustion chamber to separate, the separation obstructs the incoming flow, and a quasi-positive shock wave string is formed in the isolation section. After the compression and deceleration of the quasi-normal shock wave string, the incoming flow enters the combustion chamber at the subsonic speed, and is mixed and combusted with the fuel. Under the combined action of combustion heat release and the area of a combustion chamber, the fuel gas forms heat choking at the throat of the Laval nozzle. After passing through the section, the fuel gas is recovered into supersonic airflow and generates thrust through the jet pipe; in the mixed combustion mode (4 is not less than Ma <6), along with the increase of the flight Mach number, in order to avoid the limitation of heating and total pressure loss caused by sub-combustion stamping, the heat release of combustion needs to be reduced simultaneously. The profile of the combustion chamber is adjusted into a gradually expanding section, a diffusion section and an equal straight section by the driving of a hydraulic connecting rod. Under the action of the cross section of the combustion chamber, the thermal congestion existing at the throat of the spray pipe gradually disappears, the pre-combustion shock wave string is pushed to the combustion chamber, the intensity is gradually weakened, and the flow is terminated in a supersonic flow state. Under the working mode, the core flow is supersonic, subsonic flow is formed near the concave cavities on the upper wall surface and the lower wall surface, and the sub-combustion and the super-combustion exist in the combustion chamber at the same time, so that the mixed combustion mode is presented; in the super-combustion mode (Ma is more than or equal to 6), the heat release of the combustion chamber in the combustion chamber is not enough to maintain the separation of the boundary layer, the pre-combustion shock wave string in the isolation section continuously moves into the combustion chamber until the pre-combustion shock wave string completely disappears, and the shock wave generated by the air inlet channel is reflected in the whole combustion chamber. The combustion chamber is made into an equal straight section, a gradually expanding section and a pure expansion nozzle by the driving of a hydraulic connecting rod, so that the combustion chamber is suitable for combustion heat release.
5. The hydraulic connecting rod is driven to adjust the combustion chamber profile, namely the position of the hydraulic connecting rod is adjusted by changing hydraulic pressure, the connecting rod moves along with the hydraulic connecting rod, and the hydraulic connecting rod acts on the adjustable three combustion chamber profiles through the connecting block, so that the purpose of changing the combustion chamber profiles is achieved. According to the flight Mach number, the molded surface of the combustion chamber is adjusted, and the working performance of the combustion chamber under different flight Mach numbers is ensured.
Compared with the traditional stamping combustion chamber, the invention has the following advantages:
1) the invention effectively widens the working Mach number of the bimodal ramjet engine, and the profile of the combustion chamber is driven and adjusted by the hydraulic connecting rod, so that the combustion chamber can work in different modes under different flight Mach numbers. The combustion chamber has three working modes, and the combustion chamber with 2< Ma <4 can be adjusted to be in a sub-combustion mode; ma is more than or equal to 4 and less than 6, the combustion chamber can be gradually transited from a hot choked state to be free of choked through the adjustment of the profile of the combustion chamber, meanwhile, the thrust and momentum acting on the aircraft can be stably transited, the working Mach number range of the combustion chamber is expanded, and the performance requirement on an air inlet channel is reduced; the combustion chamber with Ma less than or equal to 6 can be adjusted to be in a super-combustion mode.
2) The profile of the combustion chamber is adjusted by the driving of the hydraulic connecting rod, so that the combustion chamber has higher performance under each working mode, and the combustion chamber is in an optimal working state in wide-speed-range flight. Meanwhile, stable conversion of different combustion modes is realized.
Drawings
FIG. 1 is a block diagram of an embodiment of the present invention.
FIG. 2 is a sub-combustion mode diagram of an embodiment of the invention.
Fig. 3 is a mixed mode diagram according to an embodiment of the present invention.
FIG. 4 is a deflagration mode diagram according to an embodiment of the present invention.
Each of the labels in the figure is: 1 is an isolation section, 2 is an upper wall face pioneer hydrogen injection module, 3 is an upper wall face kerosene injection module, 4 is a sudden expansion section, 5 is a first adjustable variable section, 6 is a first hydraulic drive, 7 is a first connecting rod, 8 is a first connecting block, 9 is a second hydraulic drive, 10 is a second connecting rod, 11 is a second connecting block, 12 is a third adjustable variable section, 13 is a lower wall face pioneer hydrogen injection module, 14 is a lower wall face kerosene injection module, 15 is a cavity, 16 is a combustion chamber lower wall face, 17 is a second adjustable variable section, and 18 is a spark plug.
Detailed Description
The preferred embodiments of the present invention will be described below with reference to the accompanying drawings, i.e., the preferred embodiments described herein are merely for the purpose of illustrating and explaining the present invention, and are not intended to limit the present invention.
As shown in fig. 1 to 4, the variable-structure dual-mode combustion chamber of the embodiment of the invention comprises an isolation section 1, a sudden expansion section 4, a cavity 15, a lower wall surface 16 of the combustion chamber, a first adjustable deformation section 5, a second adjustable deformation section 17 and a third adjustable deformation section 12. The isolation section 1 and the sudden expansion section 4 are connected through bolts. The upper and lower wall surface pioneer hydrogen injection modules 2 and 13 and the upper and lower kerosene injection modules 3 and 13 are fixed on the sudden expansion section 4 through bolts, and the first adjustable deformation section 5, the second adjustable deformation section 17, the third adjustable deformation section 12 and the sudden expansion section 4 are fixedly connected through flanges. The first hydraulic drive 6 and the second hydraulic drive 9 act on the first adjustable deformation section 5 and the third adjustable deformation section 12 through a first connecting rod 7, a first connecting block 8, a second connecting rod 10 and a second connecting block 11, respectively.
When the variable-structure dual-mode combustion chamber works, air entering the isolation section 1 is mixed with the pioneer hydrogen and kerosene sprayed by the upper wall surface pioneer hydrogen spraying module 2, the lower wall surface pioneer hydrogen spraying module 13, the upper wall surface kerosene spraying module 3 and the lower wall surface kerosene spraying module 14, and is ignited through the spark plug 18 in the concave cavity 15. The sudden expansion section 4 and the cavity 15 can maintain the stable flame tissue to be combusted and then are discharged from an adjustable nozzle consisting of the first adjustable variable section 5, the second adjustable variable section 17 and the third adjustable variable section 12 to generate thrust;
the variable structure combustion chamber works in different states along with the change of the flight Mach number in the flight process, and the hydraulic drives 6 and 9 change the positions of the first adjustable variable section 5, the second adjustable variable section 17 and the third adjustable variable section 12 through the connecting rods 7 and 10 and the connecting blocks 8 and 11 to change the profiles of the combustion chamber.
In the sub-combustion mode, shown in fig. 2, in which the mach number is greater than 2.0 and less than 4.0, the first hydraulic drive 6 changes the position of the first adjustable segment 5 through the first connecting rod 7 and the first connecting block 8. The second hydraulic drive 9 changes the position of the third adjustable variable section 12 via a second connecting rod 10 and a second connecting block 11. The first adjustable variable section 5 and the third adjustable variable section 12 are adjusted to drive the second adjustable variable section, so that the profile of the combustion chamber is changed. The profile of the combustion chamber consists of an equal straight section and a gradually expanding section, and the tail nozzle is a Laval nozzle; under the combined action of combustion heat release and the area of a combustion chamber, the fuel gas forms heat choking at the throat of the Laval nozzle. After passing through the section, the fuel gas is recovered into supersonic airflow and generates thrust through the jet pipe;
in the mixed mode, when the mach number is greater than or equal to 4.0 and less than 6.0, the first hydraulic drive 6 changes the position of the first adjustable variable section 5 through the first connecting rod 7 and the first connecting block 8, as shown in fig. 3. The second hydraulic drive 9 changes the position of the third adjustable variable section 12 via a second connecting rod 10 and a second connecting block 11. The first adjustable variable section 5 and the third adjustable variable section 12 are adjusted to drive the second adjustable variable section, so that the profile of the combustion chamber is changed. The profile of the combustion chamber consists of an equal straight section, a diffusion section and an equal straight section. Under the action of the cross section of the combustion chamber, the thermal congestion existing at the throat of the spray pipe gradually disappears, the pre-combustion shock wave string is pushed to the combustion chamber, the intensity is gradually weakened, and the flow is terminated in a supersonic flow state. Under the working mode, the core flow is supersonic, subsonic flow is formed near the concave cavities on the upper wall surface and the lower wall surface, and the sub-combustion and the super-combustion exist in the combustion chamber at the same time, so that the mixed combustion mode is presented;
in the scramjet mode, when the mach number is greater than or equal to 6.0, the first hydraulic drive 6 changes the position of the first adjustable variable section 5 through the first connecting rod 7 and the first connecting block 8, as shown in fig. 4. The second hydraulic drive 9 changes the position of the third adjustable variable section 12 via a second connecting rod 10 and a second connecting block 11. The first adjustable variable section 5 and the third adjustable variable section 12 are adjusted to drive the second adjustable variable section, so that the profile of the combustion chamber is changed. The combustion chamber profile is composed of an equal straight section, a diffusion section and a pure expansion nozzle. The flow in the combustion chamber is in a supersonic flow state.
The invention can effectively improve the working performance of the combustion chamber of the variable-structure bimodal ramjet engine under the wide Mach number, improve the thermal efficiency and the fuel specific impulse, reduce the afterburning oil consumption, improve the flight range and expand the high-efficiency working Mach number range of the combustion chamber.
Claims (6)
1. A variable-structure bimodal stamping combustion chamber is characterized by comprising an isolation section, a concave cavity, a sudden expansion section, an adjustable variable section, a pioneer hydrogen injection module, a kerosene injection module, a connecting rod and a hydraulic drive;
the isolation section, the sudden expansion section and the adjustable deformation section are sequentially connected, and the isolation section and the sudden expansion section form a fixed section; the pioneer hydrogen module and the kerosene injection module are fixed on the sudden expansion section and are used for injecting hydrogen and kerosene; the concave cavity is arranged on the lower wall surface of the combustion chamber, and the bottom of the concave cavity is provided with a spark plug for ignition; the hydraulic drive acts on the adjustable variable section through the connecting rod, and the profile of the combustion chamber is adjusted through the hydraulic drive, so that the combustion chamber works in different modes under different flight Mach numbers.
2. The variable structure dual-mode stamping combustion chamber as claimed in claim 1, wherein the adjustable deformation sections include a first adjustable deformation section, a second adjustable deformation section and a third adjustable deformation section, and the adjustable deformation sections are fixedly connected through a connecting flange; the first hydraulic drive and the first connecting rod are connected with the first adjustable variable section through a first connecting block; and the second hydraulic drive and the second connecting rod are connected with the third adjustable variable section through a second connecting block.
3. The variable geometry dual-mode ramjet combustor of claim 1, wherein said combustor operates in different modes at different mach numbers of flight, including a sub-combustion mode, a mixed mode and a super-combustion mode.
4. The variable geometry dual-mode ramjet combustor of claim 3, wherein in the sub-combustion mode, at a Mach number greater than 2.0 and less than 4.0, the variable geometry position is changed by hydraulic actuation via the connecting rod and the connecting block to adjust the combustion chamber profile to an equal straight section and a diverging section, and the tailpipe is a lava nozzle.
5. The variable geometry dual-mode ramjet combustor of claim 3, wherein in the mixed mode, at a mach number of 4.0 or more and less than 6.0, the variable geometry section is hydraulically driven through the connecting rod and the connecting block to change the position of the variable geometry section, thereby adjusting the combustion chamber profile to be a constant straight section, a diffuser section and a constant straight section.
6. The variable-structure dual-mode ram combustor of claim 3, wherein in the scramjet mode, when the Mach number is greater than or equal to 6.0, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block so as to adjust the profile of the combustor into an equal straight section, a diffusion section and a pure expansion nozzle.
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Cited By (4)
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| CN114484503A (en) * | 2022-01-05 | 2022-05-13 | 中国科学院力学研究所 | Self-adaptive geometric throat combustion chamber of wide-range ramjet engine |
| CN114528769A (en) * | 2022-02-25 | 2022-05-24 | 中国空气动力研究与发展中心空天技术研究所 | Intelligent monitoring method and system for combustion mode of scramjet engine |
| CN115585480A (en) * | 2022-08-26 | 2023-01-10 | 中国航天空气动力技术研究院 | Wide-adaptability supersonic combustion chamber with adjustable concave cavity structure |
| CN116221778A (en) * | 2023-02-28 | 2023-06-06 | 中国人民解放军32804部队 | Supersonic combustion chamber plasma ignition device and method based on boundary layer air entraining |
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