CN117663195A - A ladder-shaped large-range flow adjustment rotating detonation combustion device - Google Patents

Abstract

The invention provides a stepped large-range flow-regulating rotary detonation combustion device which comprises an outer ring injection device, an annular flow passage, a central injection device, a central disc flow passage, a central inner column, an annular diversion cone and the like. The combustion device comprises 1 annular combustion chamber and N central disc type combustion chambers, combustion products of the annular combustion chambers expand along the axial direction, the combustion products of the central disc type combustion chambers expand along the radial direction, the combustion products become expanded along the axial direction of the annular flow passage downwards after passing through the annular flow guide cone, and a plurality of detonation combustion products are converged at the downstream of the annular flow passage and pass through an outlet of the combustion device. According to the invention, N central disk type combustion chambers are axially arranged on the central inner column, so that the fuel/oxidant flow regulation range can be enlarged, and the space utilization rate and the working capacity of the combustion device can be improved. In addition, air or fuel supplied to the central disk burner may form a cooling film through cooling holes in the central inner post for cooling the central inner post or plug nozzle, improving the heat protection capability of the burner.

Description

A ladder-shaped large-range flow adjustment rotating detonation combustion device

Technical field

The invention relates to the technical field of rotating detonation propulsion, and is specifically a ladder-shaped large-range flow adjustment rotating detonation combustion device.

Background technique

Compared with traditional slow-burn combustion, detonation combustion has the advantages of fast energy release rate and high thermal cycle efficiency, and is expected to improve the propulsion performance of jet engines.

Rotating detonation combustion chambers mainly include annular combustion chambers, hollow combustion chambers and central disc combustion chambers. In the annular combustion chamber and the hollow combustion chamber, the oxidant and fuel are supplied axially by the injection unit at the head of the combustion chamber, and the rotating detonation wave propagates in the circumferential direction; in the central disk combustion chamber, the oxidant and fuel are supplied by the combustion device The injection units arranged in the periphery or center are supplied in the radial direction, and the rotational detonation wave also propagates in the circumferential direction.

However, the engineering applications of annular combustion chambers and central disc combustion chambers still face many problems. An annular combustion chamber usually contains a central inner column and an annular channel in which the combustion products expand axially downstream. Normally, the central inner column occupies too much space in the combustion chamber, and the fuel and oxidizer are only burned in the head area of the combustion chamber, making it difficult to organize large-flow combustion. At the same time, the central inner column is exposed to high-temperature combustion products for a long time and faces severe thermal protection problems. The central disk combustion chamber has the advantage of short axial length, but combustion is not organized in the central area, resulting in low space utilization and difficulty in establishing high chamber pressure. In addition, when only an annular combustion chamber or a central disk combustion chamber is used, the thrust adjustment range is small, and it cannot provide the short-term large thrust with the same effect of afterburning, and cannot meet the aircraft's demand for short-term large acceleration.

Therefore, in view of the above problems, it is particularly important to design a combustion device that can increase the space utilization of the combustion chamber and expand the fuel/oxidant flow adjustment range. The present invention proposes a stepped large-range flow-adjusted combustion rotary detonation device, which can meet the above requirements and has practical value in the actual application of rotary detonation engines.

Contents of the invention

Aiming at the problem that the annular combustion chamber has low space utilization and the fuel/oxidant flow rate cannot be adjusted in a wide range, the present invention proposes a stepped-shaped large-range flow adjustment rotating detonation combustion device, which adjusts the flow rate in the center on the basis of the annular combustion chamber. The column is optimized and improved, and N central disk-type combustion chambers distributed along the axial direction are arranged on the central inner column to expand the fuel/oxidant adjustment range, thereby expanding the thrust adjustment range. The invention can be applied to the technical fields of detonation combustion and aerospace propulsion.

In order to achieve the above objects, the present invention adopts the following technical solutions:

A ladder-shaped large-range flow adjustment rotating detonation combustion device, including an outer ring injection device, an annular flow channel, a central injection device, a central disc flow channel, a central inner column, a central fuel/oxidant supply pipeline, and annular guides. Flow cone and high energy ignition device.

The annular combustion chamber and the central disk combustion chamber of the combustion device are distributed in a ladder shape along the radial direction, and the central disk combustion chamber is located on the central inner column and arranged along the axial direction. Each combustion chamber works independently to achieve multi-stage zoned combustion. .

The injection device includes an outer ring injection device and a central injection device, both of which are composed of multiple groups of injection units evenly distributed in the circumferential direction. Both the outer ring injection unit and the central injection unit should select appropriate mixing methods based on the physical properties of the fuel and oxidant, supply flow rate, injection pressure drop and other actual needs, such as coaxial centrifugal, annular slot injection holes, orifices. Mixing methods such as hole impact or high-speed jet injection. The reactants are fully mixed after being injected by the injection unit, and then rotate and detonate to cause combustion.

The width h of the annular flow channel should be no less than 3 times the average cell size λ _a , the axial length of the annular flow channel should be no less than 13 times the average cell size λ _a ; the inner diameter r _i1 of the annular combustion channel should be no less than 14 times the average cell size λ _a ; the inner diameter r _i2 of the central disc flow channel is not less than 23 times the average cell size λ _a , ensuring that the rotating detonation wave can maintain stable propagation in the annular flow channel and the central disc flow channel.

In addition to the continuous and stable propagation of the rotating detonation wave, the central disc flow channel should also work with the annular flow guide cone to cause the combustion products to change from radial expansion to axial expansion downstream of the annular flow channel. In addition, there are a total of N central disc flow channels, which are located on the central inner column and arranged axially along the central inner column. The outlet of the central disc flow channel should also be parallel to the central axis and distributed in a stepped manner from the upstream to the downstream of the outer wall of the annular flow channel to ensure that the detonation combustion products of each central disc combustion chamber also interact with each other after leaving the central disc flow channel. Parallel layered flow.

The central fuel/oxidant supply pipeline is connected to the fuel chamber and oxidation chamber of the central disc combustion chamber, and is at a certain distance from the central axis of the central inner column, so that the area close to the central axis can be arranged to connect the compressor and the turbine transmission Rod.

The high-energy ignition device of the annular combustion chamber is arranged on the outer wall of the annular flow channel, about 1/6 of the axial length of the annular flow channel from the injection device; the high-energy ignition device of the central disk-type combustion chamber is arranged on the end face of the head of the combustion chamber, located on the center disk A certain position at 1/2 of the radial length of the type flow channel. The high-energy ignition device should be able to provide high-energy ignition energy to ignite the fuel and oxidizer so that the detonation wave can stably propagate in the circumferential direction.

Beneficial effects:

The invention is a stepped-shaped large-range flow-adjusted rotating detonation combustion device. The combustion device includes an annular combustion chamber and N central disk-type combustion chambers located on the central inner column and arranged along the axial direction. The two combustion chambers are arranged along the axial direction. It is distributed in a ladder shape in the radial direction and can organize rotating detonation combustion in zones. The combustion products in the annular combustion chamber directly pass through the annular flow channel. The combustion products in the central disc combustion chamber merge into the annular flow channel in parallel layers. Multiple streams of combustion products After the flow merges, it drives the turbine to do work or accelerates the expansion of the nozzle to form a high-speed airflow to generate thrust. This combustion device greatly improves the space utilization of the annular combustion chamber by improving the central inner column structure. In addition, compared with the annular combustion chamber, the stepped large-range flow adjustment combustion chamber can greatly expand the flow adjustment range of the fuel/oxidant used to organize rotating detonation combustion, thereby expanding the thrust adjustment range of the propulsion device.

Description of drawings

Figure 1 is a cross-sectional view of a ladder-shaped large-range flow adjustment rotary detonation combustion device provided by the present invention;

Figure 2 is a front view of the head of the stepped large-range flow adjustment rotary detonation combustion device provided by the present invention;

Figure 3 is a J-J cross-sectional view with a nozzle of the stepped large-range flow adjustment rotary detonation combustion device provided by the present invention;

Figure 4 is a G-G cross-sectional view of the stepped large-range flow adjustment rotary detonation combustion device with a nozzle provided by the present invention;

Among them, 1 is the annular combustion chamber fuel injection hole, 2 is the annular combustion chamber oxidizer injection annular gap, 3 is the annular guide cone, 4 is the annular combustion chamber high-energy ignition device, 5 is the annular flow channel, and 6 is the central disk combustion Chamber high-energy ignition device, 7 is the central inner column, 8 is the central disc combustion chamber oxidizer chamber, 9 is the central disc combustion chamber fuel chamber, 10 is the central disc flow channel, 11 is the central oxidant supply pipeline, and 12 is the center In the fuel supply pipeline, 13 is the pneumatic inner column of the plug nozzle, and 14 is the plug nozzle.

Detailed ways

The present invention will now be further described in conjunction with the accompanying drawings:

Referring to Figures 1 to 2, the present invention is a stepped large-range flow adjustment rotating detonation combustion device, including an annular flow channel 5, a central disk flow channel 10, annular guide cone 3, etc. This combustion device can organize rotating detonation combustion in the annular combustion chamber and the central disk combustion chamber respectively, realizing zoning and multi-stage combustion of the combustion device, effectively improving the space utilization of the combustion device, expanding the fuel/oxidant flow adjustment range, and thus expanding the propulsion The device's thrust adjustment range improves propulsion performance.

Referring to Figure 1, in the annular combustion chamber, fuel and oxidizer are injected into the annular flow channel 5 through the injection device and are atomized and mixed. The high-energy ignition device 4 of the annular combustion chamber is subsequently ignited. After successfully organizing detonation combustion, the detonation wave circulates in the annular The flow channel 5 propagates stably along the circumferential direction. In the central disk combustion chamber, there is a small flow operating state in which the central disk combustion chamber does not organize rotational detonation combustion and a large flow operating state in which M (M ≤ N) central disk combustion chambers organize rotational detonation combustion. The detonation combustion products in the central disc combustion chamber undergo the joint action of the central disc flow channel 10 and the annular guide cone 3, and change from radial expansion to axial expansion downstream and merge into the annular flow channel 5. Multiple combustion products converge. Then it continues to expand axially downstream and pushes the turbine blades to do work, or directly flows into the nozzle to expand and accelerate to form a high-speed airflow to generate thrust.

Example 1:

Referring to Figure 1, the combustion device works in a low flow state. The fuel nozzle hole 1 of the annular combustion chamber and the oxidant annular gap 2 of the annular combustion chamber inject fuel and oxidizer into the annular flow channel 5 and atomize and mix them, and then ignite with high energy through the annular combustion chamber. After device 4 is ignited, the tissue rotates, detonates and burns. If the propulsion device is a turbojet configuration or an air-breathing ram configuration, air is injected into the annular flow channel 5 through the cooling holes on the central inner column 7, and forms a stepped cooling air film on the outer wall of the central inner column 7; If the propulsion device is in a rocket configuration, low-temperature fuel is injected into the annular flow channel 5 through the cooling holes on the central inner column 7 , and a stepped cooling liquid film is also formed on the outer wall of the central inner column 7 . The cooling film can prevent high-temperature combustion products from damaging the outer wall of the annular flow channel 5, and can also cool the plug nozzle. The combustion products leave the combustion chamber and drive the turbine to do work. Referring to Figure 3, after a plug nozzle 14 is installed behind the combustion chamber, the combustion products can be accelerated through the expansion of the nozzle to generate thrust.

Example 2:

Combining Figures 1 and 2, the combustion device works in a large flow state. In Example 1, on the basis of the stable operation of the annular combustion chamber and the normal outflow of the cooling air film, fuel or oxidant is supplied to the central disk combustion chamber at the same time. The flow channel 10 is fully atomized and ignited to organize rotational detonation combustion. According to the actual required thrust of the aircraft, the central disc combustion chamber P ₁ , P ₂ ... _PM can organize rotational detonation combustion at the same time. When the annular combustion chamber and M central disk combustion chambers organize combustion at the same time, the fuel/oxidant supply flow rate of the combustion device is greatly increased, and the corresponding thrust is also greatly increased. When the thrust range needs to be adjusted over a wide range, the fuel/oxidizer supply flow rate also needs to be adjusted over a wide range accordingly. When the required thrust increases, the central disk combustion chamber PM ₊₁ , PM ₊₂ , PM ₊₃ ... supplies fuel/oxidant and organizes combustion; when the required thrust decreases, the central disk combustion chamber _{PM- 1} , PM _-2 , _PM-3 ... Stop supplying fuel/oxidant and terminate combustion. By organizing rotating detonation combustion in different numbers of central disc combustion chambers, the fuel/oxidizer supply flow of the combustion device can be adjusted within a wide range, thereby adjusting the required thrust of the aircraft within a wide range.

The invention has important value for the practical application of rotating detonation combustion mode. Those skilled in the art can make various changes and optimizations to the above method without departing from the principles of the present invention.

Claims (5)

1. A stepped large-range flow-regulating rotary detonation combustion device comprises an outer ring injection device, an annular flow passage, a central injection device, a central disk flow passage, a central inner column, a central fuel/oxidant supply pipeline, an annular diversion cone and an ignition device. The annular combustion chamber and the central disc type combustion chamber of the combustion device are distributed in a stepped manner along the radial direction, the central disc type combustion chamber is positioned on the central inner column and is axially arranged, the two combustion chambers work independently, combustion products of the two combustion chambers are converged in the annular flow passage and continuously expand along the axial downstream direction, and therefore the space utilization rate of the combustion device can be improved, the fuel/oxidant flow regulation range is enlarged, and the function doing capability is improved.

2. The stepped large-scale flow-regulated rotary detonation combustion device of claim 1, wherein: the injection device comprises a plurality of groups of injection units which are circumferentially and uniformly distributed, the fuel injection units and the oxidant injection units are used for selecting proper atomization mixing modes such as circular seam spray holes, two-strand impact and coaxial centrifugation according to the physical properties, the supply flow and the injection pressure drop of fuel/oxidant, reactants are impacted and fully mixed after passing through the fuel/oxidant injection units, and the reactants are ignited by a high-energy ignition device to form rotary detonation combustion of a tissue.

3. The stepped large-scale flow-regulated rotary detonation combustion device of claim 1, wherein: the width h of the annular flow channel is not less than 3 times of the average cell size lambda _a The method comprises the steps of carrying out a first treatment on the surface of the The axial length of the annular flow channel is not less than 13 times of the average cell size lambda _a The method comprises the steps of carrying out a first treatment on the surface of the Annular combustion chamberInner diameter r _i1 Not less than 14 times the average cell size lambda _a The method comprises the steps of carrying out a first treatment on the surface of the Inner diameter r of central disc type runner _i2 Not less than 23 times the average cell size lambda _a 。

4. The stepped large-scale flow-regulated rotary detonation combustion device of claim 1, wherein: n central disk type combustion chambers are axially arranged on the central inner column, fuel and oxidant of the central disk type combustion chambers are respectively supplied by a central fuel supply pipeline and a central oxidant supply pipeline, the two pipelines are symmetrically distributed along the central axis of the central inner column, and outlets of all the central disk type flow passages are parallel to the central axis and are radially distributed in a stepped manner, so detonation combustion products of all the central disk type combustion chambers are parallel to each other and flow in layers after leaving the central disk type flow passages, and expand axially downwards, and momentum loss of the combustion products caused by radial expansion can be avoided.

5. The stepped large-scale flow-regulated rotary detonation combustion device of claim 1, wherein: when the combustion device is in a low-flow working condition, only the annular combustion chamber is used for organizing rotary detonation combustion, and the central disc type combustion chamber stops supplying air and fuel; when the combustion device is in a high-flow working condition, the annular combustion chamber and the central disk type combustion chamber both supply fuel and oxidant and organize rotary knocking combustion, so that the fuel/oxidant flow regulation range of the combustion device can be enlarged, and the thrust regulation range is further enlarged.