A double-bend premixed preevaporation flame stabilizer

Abstract

The present application belongs to the technical field of flame stabilizer design in aircraft engines, and specifically relates to a double-bend premixed preevaporated flame stabilizer, which is a double-bend flame stabilizer that uses external airflow for cooling and premixed preevaporation with fuel. The premixed preevaporation of fuel and external airflow can be used to improve the oil-gas ratio at the trailing edge of the stabilizer, thereby improving the ignition and flame stabilization capabilities at the left boundary of the aircraft engine, and can form an air film cooling on the tail plate through two rows of cooling holes to ensure structural reliability at the right boundary of the aircraft engine and when the intake temperature is high.

Description

Technical Field

[0001] The present application belongs to the technical field of flame stabilizer design in aircraft engines, and specifically relates to a double-bend premixed preevaporation flame stabilizer. Background Art

[0002] A flame stabilizer is installed in the combustion chamber of an aircraft engine to improve the ignition flame and stable combustion capabilities of the combustion chamber.

[0003] At present, most flame stabilizers adopt V-type, special V-type, and evaporative flame stabilizers. Among them, V-type and special V-type stabilizers generally adopt a non-oil supply design, which mainly relies on the trapped vortex in the recirculation zone to draw the evaporated oil and gas near the flame transfer groove into the recirculation zone for organized combustion. The ignition and cross-flame capabilities and stable combustion capabilities at the left boundary of the aircraft engine and at low temperatures are limited; the evaporative flame stabilizer increases the fuel evaporation capacity, which can improve the ignition and cross-flame and stable combustion capabilities at the left boundary of the aircraft engine, but when the right boundary of the aircraft engine and the intake air temperature are high, there are problems such as fast fuel evaporation rate, easy spontaneous combustion, and structural damage.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0005] The purpose of the present application is to provide a double-bend premixed preevaporation flame stabilizer to overcome or alleviate at least one of the existing technical deficiencies.

[0006] The technical solution of this application is:

[0007] A double-bend premixed preevaporation flame stabilizer comprises a front cover, a tail plate, an inner cover, a partition plate, and a cover plate;

[0008] The front hood has a V-shaped cross section, open at both ends;

[0009] The tail plate is connected to the rear opening of the front cover and has two rows of cooling holes, two rows of premixed flow holes, and multiple rows of gas flow holes;

[0010] The inner cover has a rectangular or V-shaped cross section, is open at the top and blocked at the bottom, is set inside the front cover, and has a rear opening connected to the tail plate. The lower ends of the side walls on both sides have flow holes.

[0011] The partition is connected to the inner side of the inner cover, dividing the inner cover into a primary premixing chamber and a gas chamber; the premixing chamber is connected to two flow holes, and the gas chamber is connected to multiple rows of gas outflow holes;

[0012] There are two cover plates, which are arranged inside the front cover and connected to the outside of the side walls on both sides of the inner cover, forming a secondary premixing cavity between the side walls on both sides of the inner cover. The two secondary premixing cavities are connected to the two rows of premixing outflow holes;

[0013] A cooling cavity is formed between the front cover, the tail plate, the inner cover and the two cover plates, and the cooling cavity is connected to the two rows of cooling holes.

[0014] Optionally, in the above-mentioned double-bend premixing preevaporation flame stabilizer, both sides of the tail plate have outward folded edges, and the two outward folded edges are connected to the side walls on both sides of the rear opening of the front cover.

[0015] Optionally, in the above-mentioned double-bend premixed preevaporation flame stabilizer, two rows of cooling holes are located on both sides of the tail plate, two rows of premixed flow outlet holes are located between the two rows of cooling holes, and multiple rows of gas flow outlet holes are located between the two rows of premixed flow outlet holes, and the positions of the cooling holes, premixed flow outlet holes, and gas flow outlet holes are staggered in the axial direction.

[0016] Optionally, in the above-mentioned double-bend premixing preevaporation flame stabilizer, the upper section of the inner cover has a larger size than the lower section, and there is a smooth transition between the upper section and the lower section.

[0017] Optionally, in the above-mentioned double-bend premixing preevaporation flame stabilizer, the two flow holes are rectangular.

[0018] Optionally, the above-mentioned double-bend premixing preevaporation flame stabilizer further includes a diverter plate;

[0019] The diverter plate is arranged in the first-stage premixing chamber, connected to the end of the inner cover and connected to the partition plate, and is located between the two flow holes.

[0020] This application has at least the following beneficial technical effects:

[0021] Provided is a double-bend premixed preevaporation type flame stabilizer, which utilizes outer bypass airflow for cooling and premixed preevaporation with fuel. The premixed preevaporation of fuel and outer bypass airflow can be utilized to increase the oil-gas ratio at the trailing edge of the stabilizer, thereby improving the ignition flame and stable combustion capabilities at the left boundary of the aircraft engine. In addition, air film cooling can be formed on the tail plate through two rows of cooling holes, thereby ensuring structural reliability under conditions where the right boundary of the aircraft engine and the intake air temperature are high. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Schematic diagram of a double-bend premixed preevaporation flame stabilizer provided in an embodiment of the present application;

[0023] Figure 2 This is a schematic transverse cross-sectional view of a double-bend premixed preevaporation flame stabilizer provided in an embodiment of the present application;

[0024] Figure 3 is a schematic diagram of a front cover provided in an embodiment of the present application;

[0025] Figure 4 is a schematic diagram of a tailgate provided in an embodiment of the present application;

[0026] Figure 5 is a schematic diagram of an inner cover provided in an embodiment of the present application;

[0027] Figure 6 is a schematic diagram of a partition provided in an embodiment of the present application;

[0028] Figure 7 is a schematic diagram of a diverter plate provided in an embodiment of the present application;

[0029] Figure 8 is a schematic diagram of a cover plate provided in an embodiment of the present application;

[0030] in:

[0031] 1-front cover; 2-tail plate; 3-inner cover; 4-partition plate; 5-diverter plate; 6-cover plate;

[0032] A-cooling hole; B-premixed flow hole; C-gas flow hole; D-flow hole;

[0033] E-first stage premixing chamber; F-gas chamber; G-second stage premixing chamber; H-cooling chamber.

[0034] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0035] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0036] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0037] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0038] A double-bend premixed preevaporation flame stabilizer, such as Figure 1-2 As shown, it includes a front cover 1, a tail plate 2, an inner cover 3, a partition 4, a diverter plate 5, and a cover plate 6.

[0039] Front cover 1 Figure 3 As shown, the cross section is V-shaped with both ends open.

[0040] Tailgate 2 Figure 4 As shown, the tail panel 2 is connected to the rear opening of the front hood 1. Specifically, the tail panel 2 can be designed with outward-facing folds on both sides, which are connected to the inner sidewalls of the rear opening of the front hood 1. The tail panel 2 has two rows of cooling holes A, two rows of premixed flow holes B, and multiple rows of gas flow holes C. The two rows of cooling holes A are located on both sides of the tail panel 2, the two rows of premixed flow holes B are located between the two rows of cooling holes A, and the multiple rows of gas flow holes C are located between the two rows of premixed flow holes B. The cooling holes A, premixed flow holes B, and gas flow holes C are staggered in the axial direction.

[0041] Inner cover 3 Figure 5 As shown, the cross-section is rectangular or V-shaped, open at the top and closed at the bottom. It is located within the front cover 1, with the rear opening connected to the tailgate 2. The lower ends of the sidewalls on both sides have flow holes D. The upper section of the inner cover 3 is larger than the lower section, and the transition between the upper and lower sections is smooth. The two flow holes D are rectangular.

[0042] Partition 4 Figure 6 As shown, it is connected to the inner side of the inner cover 3, dividing the inner cover 3 into a primary premixing chamber E and a gas chamber F; the premixing chamber E is connected to two flow holes D, and the gas chamber F is connected to multiple rows of gas outflow holes C.

[0043] Diverter plate 5 Figure 7 As shown, it is arranged in the primary premixing chamber E, connected to the end of the inner cover 3, and connected to the partition 4, and is located between the two flow holes D.

[0044] Cover plate 6 Figure 8 As shown, there are two of them, which are arranged in the front cover 1 and connected to the outside of the side walls on both sides of the inner cover 3, forming a secondary premixing chamber G between the side walls on both sides of the inner cover 3. The two secondary premixing chambers G are connected to two rows of premixing outflow holes B.

[0045] A cooling cavity H is formed between the front cover 1 , the tail plate 2 , the inner cover 3 and the two cover plates 6 , and the cooling cavity H is connected to the two rows of cooling holes A.

[0046] The double-bend premixing and preevaporating flame stabilizer disclosed in the above embodiment can be arranged radially in the combustion chamber of an aircraft engine in a specific application, so that the upper ends of the cooling chamber H and the first-stage premixing chamber E are connected to the outer duct, and the outer duct airflow is introduced, and fuel is introduced from the upper end into the first-stage premixing chamber E and the combustion chamber F.

[0047] The external airflow entering the cooling cavity H will flow out from the two rows of cooling holes A along the way, forming a cooling air film on the tail plate 2 to cool the tail plate 2 and prevent high-temperature gas from burning on the wall, thereby avoiding structural damage.

[0048] The external airflow entering the first-stage premixing chamber E will be mixed and evaporated with the fuel entering the first-stage premixing chamber E along the way, and then deflected to the second-stage premixing chamber G through two flow holes D, further mixed and evaporated along the way, and can flow out from the two rows of premixing outflow holes B. The premixing is sufficient, and reliable ignition, cross-flame and organized combustion can be carried out in the recirculation zone formed at the trailing edge of the stabilizer.

[0049] The fuel introduced into the gas chamber F can evaporate along the way and flow out from multiple rows of gas outlet holes C, which can balance the premixed oil-gas ratio and cool the stabilizer tail plate at the same time, thereby improving the stabilizer's ignition and cross-flame and stable combustion capabilities, and preventing rapid evaporation of fuel, which can easily cause spontaneous combustion and lead to structural damage and other problems.

[0050] The double-bend premixed preevaporation type flame stabilizer disclosed in the above embodiment is a double-bend type flame stabilizer that utilizes outer flow airflow for cooling and premixed preevaporation with fuel. It can utilize the premixed preevaporation of fuel and outer flow airflow to improve the oil-gas ratio at the trailing edge of the stabilizer, thereby improving the ignition flame and stable combustion capabilities at the left boundary of the aircraft engine, and can form an air film cooling on the tail plate 2 through two rows of cooling holes A, thereby ensuring structural reliability under conditions where the right boundary of the aircraft engine and the intake air temperature are high.

[0051] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A double-bend premixed preevaporation flame stabilizer, characterized in that: It includes a front cover (1), a tail plate (2), an inner cover (3), a partition (4), and a cover plate (6); The front cover (1) has a V-shaped cross section and is open at both ends; The tail plate (2) is connected to the rear opening of the front cover (1) and has two rows of cooling holes (A), two rows of premixed flow outlet holes (B), and multiple rows of gas flow outlet holes (C); The inner cover (3) has a rectangular or V-shaped cross section, an open upper end, and a blocked lower end. It is arranged inside the front cover (1), and the rear opening is connected to the tail plate (2). The lower ends of the side walls on both sides have flow holes (D). The partition (4) is connected to the inner side of the inner cover (3), dividing the inner cover (3) into a primary premixing chamber (E) and a gas chamber (F); the premixing chamber (E) is connected to two flow holes (D), and the gas chamber (F) is connected to multiple rows of gas outflow holes (C); There are two cover plates (6), which are arranged in the front cover (1) and connected to the outside of the side walls on both sides of the inner cover (3), forming a secondary premixing cavity (G) between the side walls on both sides of the inner cover (3), and the two secondary premixing cavities (G) are connected to the two rows of premixing outflow holes (B); A cooling cavity (H) is formed between the front cover (1), the tail plate (2), the inner cover (3) and the two cover plates (6), and the cooling cavity (H) is connected to the two rows of cooling holes (A).

2. The double-bend premixed preevaporation flame stabilizer according to claim 1, characterized in that: The tail plate (2) has outward folded edges on both sides, and the two outward folded edges are connected to the side walls on both sides of the rear opening of the front cover (1).

3. The double-bend premixed preevaporation flame stabilizer according to claim 1, characterized in that: Two rows of cooling holes (A) are located on both sides of the tail plate (2), two rows of premixed flow outlet holes (B) are located between the two rows of cooling holes (A), and multiple rows of gas flow outlet holes (C) are located between the two rows of premixed flow outlet holes (B), and the positions of the cooling holes (A), premixed flow outlet holes (B), and gas flow outlet holes (C) are staggered in the axial direction.

4. The double-bend premixed preevaporation flame stabilizer according to claim 1, characterized in that: The upper section of the inner cover (3) has a larger size than the lower section, and there is a smooth transition between the upper section and the lower section.

5. The double-bend premixed preevaporation flame stabilizer according to claim 1, characterized in that: The two flow holes (D) are rectangular.

6. The double-bend premixed preevaporation flame stabilizer according to claim 1, characterized in that: Also included is a manifold (5); The diverter plate (5) is arranged in the first-stage premixing chamber (E), connected to the end of the inner cover (3), and connected to the partition plate (4), and is located between the two flow holes (D).

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