High-pass flow wide-range double-loop double-speed double-temperature collaborative combustion chamber

Abstract

The application discloses a high-throughflow wide-range double-ring double-speed double-temperature collaborative combustion chamber and relates to the technical field of aero-engine combustion chambers.The combustion chamber comprises an outer flame tube and an inner flame tube which are arranged in a sleeved mode, and an annular channel is formed between the two; a partition plate is arranged in the annular channel, and the partition plate divides the annular channel into an outer annular channel and an inner annular channel; an outer annular support plate is arranged in the outer annular channel, and a high-throughflow cyclone and a ring-vortex precombustion chamber are arranged on the outer annular support plate; an inner annular support plate is arranged in the inner annular channel, and a plurality of injection holes are arranged on the inner annular support plate; wherein the inner flame tube, the outer flame tube, the inner annular support plate and the outer annular support plate enclose the combustion chamber, the outer annular channel is used for passing in medium-speed air, and the inner annular channel is used for passing in high-temperature high-speed combustion gas. The application eliminates the large pressure loss and the required space caused by the mixing of the inner and outer ducts; the respective pressures of the two ducts are fully utilized, the space is reasonably allocated for stable combustion; the heat resistance loss is reasonably controlled, and the total pressure loss is controlled.

Description

Technical Field

[0001] This invention relates to the field of aero-engine combustion chamber technology, and more specifically to a high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber. Background Technology

[0002] The high-flow wide-range engine adopts a variable cycle overall scheme. By switching between the core engine duct and multiple ducts, it can achieve both turbofan and turbojet operating modes, taking into account the economy of low-speed subcruise, the economy and acceleration of medium-speed supersonic flight, and the demand for continuous high thrust at high speeds.

[0003] Therefore, the combustion chamber needs dual-baffle intake in turbofan mode and single intake in turbojet mode. The intake conditions are complex and variable, requiring reasonable flame stabilization methods, fuel injection mixing methods, and spatiotemporal matching and heat release reaction process control of fuel and air to achieve a high-efficiency, low-drag, and stable combustion combination. For complex intake conditions with inhomogeneous inlet velocity, temperature, and composition, high-efficiency, low-drag, and stable combustion within the effective space is necessary. Currently, existing high-flow-rate wide-range engine combustion chambers mainly suffer from the following shortcomings:

[0004] 1. The high-flow wide-range engine combustion chamber operates in front of the turbine and is less than 500mm in length. Due to its compact space, it cannot achieve longer mixing and reaction times like conventional turbofan afterburners by extending the combustion chamber length to more than 1m. Therefore, its use in high-flow wide-range engine combustion chambers will greatly increase the overall length and weight of the engine.

[0005] 2. Conventional turbofan afterburners employ a pre-mixing-then-combustion method. However, the large difference in intake velocities between the two bypass pipes in a dual-variable-combustion system results in mixing losses exceeding 2% in the pre-mixing-then-combustion method alone. Conventional pre-mixing-then-combustion methods cannot meet the low pressure loss requirements.

[0006] 3. In high-flow, wide-range engines, the intake air temperature is low, resulting in fuel evaporation and poor air-fuel mixing. Conventional swirl combustion systems exhibit strong air-fuel mixing, but their stable ignition flow rate is only 10% at low temperatures, leading to significant pressure loss. Conventional swirl combustion mechanisms cannot meet the stable ignition requirements under these intake conditions. Summary of the Invention

[0007] In view of this, the present invention provides a high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature synergistic combustion chamber, which aims to solve the technical problems in the background art mentioned above, so as to eliminate the large pressure loss and required space caused by the mixing of inner and outer ducts; make full use of the pressure of the two ducts respectively, rationally allocate space for stable flame; and achieve separate combustion, rationally control thermal resistance loss, and control total pressure loss.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] A high-flow-rate, wide-range dual-annular, dual-speed, dual-temperature synergistic combustion chamber includes:

[0010] An outer flame tube and an inner flame tube are nested together, and an annular channel is formed between the inner flame tube and the outer flame tube. One end of the annular channel is the inlet, and the other end is the outlet of the combustion chamber.

[0011] A partition is disposed within the annular channel, the partition dividing the annular channel into an outer annular channel and an inner annular channel;

[0012] An outer ring support plate is disposed within the outer ring channel. The inner edge of the outer ring support plate is connected to the partition plate, and the outer edge of the outer ring support plate is connected to the inner wall of the outer flame tube. A high-pass flow cyclone separator and a ring vortex pre-combustion chamber are respectively installed on the outer ring support plate.

[0013] An inner ring support plate is disposed within the inner ring channel. The outer edge of the inner ring support plate is connected to the partition plate, and the inner edge of the inner ring support plate is connected to the outer wall of the inner flame tube. The inner ring support plate is provided with multiple injection holes.

[0014] The inner flame tube, outer flame tube, inner ring support plate, and outer ring support plate together form a combustion chamber. The outer ring channel is used to introduce medium-speed air, and the inner ring channel is used to introduce high-temperature, high-speed combustion gas.

[0015] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has an outer flame tube and an inner flame tube arranged coaxially.

[0016] According to the high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention, the inner ring support plate includes an inner ring circumferential support plate and an inner ring longitudinal support plate. One end of the inner ring longitudinal support plate is connected to the partition plate, and the other end is connected to the outer wall of the inner flame tube. The inner ring circumferential support plate and the inner ring longitudinal support plate are alternately arranged to form the injection hole.

[0017] According to the high-pass flow wide-range dual-ring dual-speed dual-temperature synergistic combustion chamber provided by the present invention, multiple high-pass flow swirlers are provided, and the multiple high-pass flow swirlers are arranged in a ring array with the center of the outer ring support plate.

[0018] According to the high-pass flow wide-area dual-ring dual-speed dual-temperature synergistic combustion chamber provided by the present invention, the annular vortex pre-combustion chamber is located inside the plurality of high-pass flow cyclones.

[0019] The high-flow wide-range dual-ring dual-speed dual-temperature co-combustion chamber provided by the present invention has both the inlet and outlet of the combustion chamber being constricted structures.

[0020] The high-flow wide-range dual-ring dual-speed dual-temperature co-combustion chamber provided by the present invention has a cross-sectional area at the combustion chamber outlet that is larger than the cross-sectional area at the inlet.

[0021] In the high-flow-rate, wide-range dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention, the cross-sectional area of ​​the outer ring channel is larger than that of the inner ring channel.

[0022] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has an inner flame tube located at one end of the combustion chamber outlet in a gradually expanding structure.

[0023] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has a gradually expanding structure at one end of the partition plate near the outer ring support plate.

[0024] As can be seen from the above technical solution, compared with the prior art, this invention discloses a high-flow, wide-range, dual-ring, dual-speed, dual-temperature synergistic combustion chamber. Through the overall concept of synergistic organization of the outer and inner ring channels, the low-temperature, medium-speed airflow in the outer ring channel employs a central staged approach. The pre-combustion stage of the high-flow cyclone separator stabilizes the flame, while the discrete injection of the main combustion stage in the annular vortex pre-combustion chamber improves mixing efficiency, achieving high efficiency and stability in low-temperature, medium-speed combustion. In the high-temperature, high-speed gas flow in the inner ring channel, multi-point uniform injection combined with rapid fuel distribution via the inner ring support plate solves the problems of high-temperature, high-speed combustion stability and combustion efficiency. Staged and zoned combustion is organized along the circumferential and radial directions in the outer and inner ring channels according to the local lean equivalence ratio with the highest reaction rate, achieving efficient and stable combustion. To achieve stable and efficient combustion under various operating conditions, an annular vortex pre-combustion chamber is set between the outer and inner ring channels to construct a stable ignition source; a high-flow cyclone separator is used in the outer ring channel to stabilize the flame and improve the stability of the low-temperature, medium-speed outer ring flame. To ensure efficient and rapid combustion, a strong blending approach is adopted to increase the fuel-air mixing rate. Supercritical fuel injection is used, where the fuel is cooled on the inner flame tube wall before injection. This solves the problems of high inner ring flow temperature and cooling difficulties, and heats the fuel to a supercritical state. The near-gaseous low density and diffusivity of the fuel enhance the fuel-air mixing rate, eliminate the time for fuel atomization and evaporation, and shorten the time required for complete reaction. Localized strong blending is employed, with a ring vortex pre-combustion chamber arranged in the outer ring channel to create a localized flow vortex, further enhancing fuel-air mixing to achieve efficient combustion. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber provided by the present invention.

[0027] Figure 2 Provided by the present invention Figure 1 A cross-sectional view along the AA direction;

[0028] Figure 3 Provided by the present invention Figure 2 A structural diagram in use.

[0029] Wherein: 1 is the outer ring channel; 2 is the inner ring channel; 3 is the outer ring support plate; 4 is the high-pass flow cyclone separator; 5 is the annular vortex pre-combustion chamber; 6 is the inner ring longitudinal support plate; 7 is the inner ring circumferential support plate; 8 is the outer flame tube; 9 is the inner flame tube; 10 is the combustion chamber outlet; 11 is the baffle plate; 12 is the outer ring main combustion stage flame; 13 is the outer ring high-pass flow cyclone flame; 14 is the annular vortex pre-combustion chamber flame; 15 is the inner ring flame. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] See Figure 1-3 The present invention discloses a high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber, comprising: an outer flame tube 8, an inner flame tube 9, a partition 11, an outer ring support plate 3, and an inner ring support plate.

[0032] The outer flame tube 8 and the inner flame tube 9 are nested together, forming an annular channel between them. One end of the annular channel is the inlet, and the other end is the combustion chamber outlet 10.

[0033] A partition 11 is disposed within the annular channel, dividing the annular channel into an outer annular channel 1 and an inner annular channel 2. Preferably, the partition 11 is also a cylindrical structure, and the partition 11 is fixed within the annular channel by an outer annular support plate 3 and an inner annular support plate.

[0034] The outer ring support plate 3 is installed inside the outer ring channel 1. The inner edge of the outer ring support plate 3 is connected to the partition plate 11, and the outer edge of the outer ring support plate 3 is connected to the inner wall of the outer flame tube 8. A high-pass flow swirler 4 and an annular vortex pre-combustion chamber 5 are respectively installed on the outer ring support plate 3. The outer ring support plate 3 can achieve flame stabilization of the outer ring main combustion stage; the high-pass flow swirler 4 can create a low-speed recirculation zone to achieve overall flame stabilization of the outer ring; and the annular vortex pre-combustion chamber 5 can achieve ignition and flame stabilization of the entire combustion chamber.

[0035] The inner ring support plate is installed inside the inner ring channel 2. The outer edge of the inner ring support plate is connected to the partition plate 11, and the inner edge of the inner ring support plate is connected to the outer wall of the inner flame tube 9. The inner ring support plate is provided with multiple injection holes. The inner ring support plate can achieve inner ring flame stabilization.

[0036] The combustion chamber is formed by the inner flame tube 9, the outer flame tube 8, the inner ring support plate, and the outer ring support plate 3. The outer ring channel 1 is used to introduce medium-speed air, and the inner ring channel 2 is used to introduce high-temperature and high-speed gas.

[0037] It should be noted that during use, this invention forms an outer ring main combustion stage flame 12, an outer ring high-pass swirling flame 13, a ring vortex pre-combustion chamber flame 14, and an inner ring flame 15 within the combustion chamber. It employs a dual-ring structure (outer ring channel 1 and inner ring channel 2) to separately organize flow and combustion, based on the overall concept of dual-ring dual-speed. This is achieved by using adjustable inner ring support plates for high-speed flow in the inner ring channel 2 and a high-pass swirling device 4 for medium-speed flow in the outer ring channel 1. After combustion with independent temperature rises in each ring, the velocity and static pressure of the two incoming flows are controlled to be nearly identical. This eliminates the large pressure loss and space requirements caused by mixing of the inner and outer rings; fully utilizes the pressure of each of the two channels; rationally allocates space for flame stabilization; and achieves separate combustion, rationally controlling thermal resistance loss and overall pressure loss.

[0038] Furthermore, through the overall concept of coordinated organization of outer ring channel 1 and inner ring channel 2, the low-temperature, medium-speed airflow in outer ring channel 1 employs a central staged combustion approach. The pre-combustion stage stabilization of the high-pass flow cyclone separator 4, combined with the discrete injection of the main combustion stage in the annular vortex pre-combustion chamber 5 to improve mixing efficiency, achieves high efficiency and stability in low-temperature, medium-speed combustion. In the high-temperature, high-speed gasflow in inner ring channel 2, multi-point uniform injection combined with rapid fuel distribution via the inner ring circumferential support plate 7 and inner ring longitudinal support plate 6 solves the problems of stable high-temperature, high-speed combustion and combustion efficiency. Staged and zoned combustion is organized along the circumferential and radial directions in outer ring channel 1 and inner ring channel 2 according to the local lean equivalence ratio with the highest reaction rate, achieving efficient and stable combustion.

[0039] To achieve stable and efficient combustion under various operating conditions, a ring vortex pre-combustion chamber 5 is installed between the outer ring channel 1 and the inner ring channel 2 to create a stable ignition source. A high-flow cyclone separator 4 is used in the outer ring channel 1 to stabilize the flame and improve the stability of the outer ring flame at low temperature and medium speed. To ensure efficient and rapid combustion, a strong mixing concept is adopted to increase the fuel-air mixing rate. Supercritical fuel injection is used, where the fuel cools the inner flame tube 9 wall before injection, solving the problems of high inner ring inflow temperature and cooling difficulties, and heating the fuel to a supercritical state. The near-gaseous low density and diffusivity of the fuel enhance the fuel-air mixing rate, eliminating the time for fuel atomization and evaporation, and shortening the time required for complete reaction. Local strong mixing is employed, with a ring vortex pre-combustion chamber 5 arranged in the outer ring channel 1 to create a local flow vortex, further enhancing fuel-air mixing to achieve efficient combustion.

[0040] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has an outer flame tube 8 and an inner flame tube 9 arranged coaxially.

[0041] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature synergistic combustion chamber provided by the present invention includes an inner ring support plate comprising an inner ring circumferential support plate 7 and an inner ring longitudinal support plate 6. One end of the inner ring longitudinal support plate 6 is connected to a partition plate 11, and the other end is connected to the outer wall of the inner flame tube 9. The inner ring circumferential support plate 7 and the inner ring longitudinal support plate 6 are staggered to form injection holes. In this embodiment, preferably, the inner ring circumferential support plate 7 and the inner ring longitudinal support plate 6 are configured as a detachable structure for adjusting the size of the injection holes. Specifically, multiple slots are provided on the inner ring longitudinal support plate 6, and multiple slots are also provided on the inner ring circumferential support plate 7. The slots on the inner ring circumferential support plate 7 can cooperate with the slots on the inner ring longitudinal support plate 6 to allow the inner ring circumferential support plate 7 to be detachably installed on the inner ring longitudinal support plate 6 as needed.

[0042] The high-flow wide-range dual-ring dual-speed dual-temperature co-combustion chamber provided by the present invention includes multiple high-flow swirlers 4, which are arranged in a ring array around the center of the outer ring support plate 3. The arrangement of multiple high-flow swirlers 4 can further construct a low-speed recirculation zone to achieve overall flame stabilization of the outer ring.

[0043] According to the high-flow wide-range dual-ring dual-speed dual-temperature synergistic combustion chamber provided by the present invention, the annular vortex pre-combustion chamber 5 is located inside multiple high-flow swirlers 4. Preferably, the annular vortex pre-combustion chamber 5 is located at the connection between the outer ring support plate 3 and the partition plate 11, and the annular vortex pre-combustion chamber 5 has an annular structure, realizing ignition and flame stabilization of the entire combustion chamber.

[0044] The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber provided by this invention features a constricted inlet and outlet 10, respectively, to achieve combustion stability.

[0045] The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber provided by this invention has a combustion chamber outlet 10 with a cross-sectional area larger than the inlet cross-sectional area, ensuring complete combustion.

[0046] The high-flow-rate, wide-range dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has an outer ring channel 1 with a cross-sectional area larger than that of the inner ring channel 2.

[0047] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has an inner flame tube 9 located at one end of the combustion chamber outlet 10, which is a gradually expanding structure.

[0048] The high-flow-rate, wide-range, dual-ring, dual-speed, dual-temperature co-combustion chamber provided by the present invention has a gradually expanding structure at one end of the partition 11 near the outer ring support plate 3.

[0049] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0050] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A high-flow-rate, wide-range dual-annular, dual-speed, dual-temperature synergistic combustion chamber, characterized in that, include: An outer flame tube and an inner flame tube are nested together, and an annular channel is formed between the inner flame tube and the outer flame tube. One end of the annular channel is the inlet, and the other end is the outlet of the combustion chamber. A partition is disposed within the annular channel, the partition dividing the annular channel into an outer annular channel and an inner annular channel; An outer ring support plate is disposed within the outer ring channel. The inner edge of the outer ring support plate is connected to the partition plate, and the outer edge of the outer ring support plate is connected to the inner wall of the outer flame tube. A high-pass flow cyclone separator and a ring vortex pre-combustion chamber are respectively installed on the outer ring support plate. The ring vortex pre-combustion chamber is located inside the high-pass flow cyclone separator and between the outer ring channel and the inner ring channel. An inner ring support plate is disposed within the inner ring channel. The outer edge of the inner ring support plate is connected to the partition plate, and the inner edge of the inner ring support plate is connected to the outer wall of the inner flame tube. The inner ring support plate is provided with multiple injection holes. The inner flame tube, outer flame tube, inner ring support plate, and outer ring support plate together form a combustion chamber. The outer ring channel is used to introduce medium-speed air, and the inner ring channel is used to introduce high-temperature, high-speed combustion gas.

2. The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 1, characterized in that, The outer flame tube and the inner flame tube are arranged coaxially.

3. The high-flow-rate, wide-range dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 1 or 2, characterized in that, The inner ring support plate includes an inner ring circumferential support plate and an inner ring longitudinal support plate. One end of the inner ring longitudinal support plate is connected to the partition plate, and the other end is connected to the outer wall of the inner flame tube. The inner ring circumferential support plate and the inner ring longitudinal support plate are staggered to form the injection hole.

4. The high-flow-rate, wide-range dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 2, characterized in that, The high-pass flow cyclone is provided in multiple forms, and the multiple high-pass flow cyclones are arranged in a ring array with the center of the outer ring support plate.

5. The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 1, characterized in that, Both the inlet and the outlet of the combustion chamber are constricted structures.

6. The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 5, characterized in that, The cross-sectional area of ​​the combustion chamber outlet is larger than the cross-sectional area of ​​the inlet.

7. The high-flow-rate, wide-range dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 1, characterized in that, The cross-sectional area of ​​the outer ring channel is larger than that of the inner ring channel.

8. The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 1, characterized in that, The inner flame tube located at one end of the combustion chamber outlet has a gradually expanding structure.

9. The high-flow-rate, wide-range, dual-annular, dual-speed, dual-temperature synergistic combustion chamber according to claim 1, characterized in that, The structure of the partition plate near the outer ring support plate is a gradually expanding structure.

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