Double-baffling premixing pre-evaporation type flame stabilizer

Abstract

The invention belongs to the technical field of design of flame stabilizers in aero-engines, and particularly relates to a double-baffling premixing and pre-evaporation type flame stabilizer which is cooled through outer culvert airflow and premixed and pre-evaporated with fuel oil, the fuel oil and outer culvert airflow can be premixed and pre-evaporated, the oil-gas ratio of the tail edge of the stabilizer can be increased, and the service life of the stabilizer is prolonged. And therefore, the ignition cross flame and stable combustion capacity at the left boundary of the aero-engine can be improved, air film cooling can be formed on the tail plate through the two rows of cooling holes, and the structural reliability at the right boundary of the aero-engine and under the condition that the air inlet temperature is high is guaranteed.

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 type 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 are V-shaped, special V-shaped, and evaporative flame stabilizers. Among them, V-shaped and special V-shaped 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 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-baffled premixed preevaporation flame stabilizer to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of this application is: A double-baffle premixed preevaporation type flame stabilizer, comprising a front cover, a tail plate, an inner cover, a partition plate, and a cover plate; The front cover is V-shaped in cross section, open at both ends; 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; The inner cover has a rectangular or V-shaped cross section, is open at the upper end and blocked at the lower end, is arranged inside the front cover, has a rear opening connected to the tail plate, and has flow holes at the lower ends of the side walls on both sides; 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; There are two cover plates, which are arranged in the front cover and connected to the outside of the side walls on both sides of the inner cover, and form a secondary premixing chamber between the side walls on both sides of the inner cover. The two secondary premixing chambers are connected to the two rows of premixing outflow holes; 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 with two rows of cooling holes.

[0007] Optionally, in the above-mentioned double-bend premixing preevaporation type flame stabilizer, there are outward folded edges on both sides of the tail plate, and the two outward folded edges are connected to the side walls on both sides of the rear opening of the front cover.

[0008] 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.

[0009] Optionally, in the above-mentioned double-bend premixed 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.

[0010] Optionally, in the above-mentioned double-bend premixing preevaporation type flame stabilizer, the two flow holes are rectangular.

[0011] Optionally, the above-mentioned double-bend premixed preevaporation type flame stabilizer further includes a splitter plate; The splitter plate is arranged in the primary premixing chamber, connected to the end of the inner cover and connected to the partition plate, and is located between the two flow holes.

[0012] This application has at least the following beneficial technical effects: Provided is a double-baffle premixed preevaporation type flame stabilizer, which is a double-baffle type flame stabilizer that utilizes an outer bypass airflow for cooling and premixes and preevaporates with fuel. The premixed preevaporation of fuel and the outer bypass airflow can be utilized to increase the oil-gas ratio at the trailing edge of the stabilizer, thereby being able to improve the ignition flame linkage and stable combustion 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, thereby ensuring the structural reliability at the right boundary of the aircraft engine and when the intake temperature is high. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 Schematic diagram of a double-bend premixed preevaporation flame stabilizer provided in an embodiment of the present application; Figure 2 It is a schematic diagram of a transverse cross-sectional view of a double-bend premixed preevaporation type flame stabilizer provided in an embodiment of the present application; Figure 3 is a schematic diagram of a front cover provided in an embodiment of the present application; Figure 4 is a schematic diagram of a tailgate provided in an embodiment of the present application; Figure 5 is a schematic diagram of an inner cover provided in an embodiment of the present application; Figure 6 is a schematic diagram of a partition provided in an embodiment of the present application; Figure 7 is a schematic diagram of a diverter plate provided in an embodiment of the present application; Figure 8 is a schematic diagram of a cover plate provided in an embodiment of the present application; in: 1-front cover; 2-tail plate; 3-inner cover; 4-partition plate; 5-diverter plate; 6-cover plate; A-cooling hole; B-premixed flow hole; C-gas flow hole; D-flow hole; E-first stage premixing chamber; F-fuel gas chamber; G-second stage premixing chamber; H-cooling chamber.

[0014] In order to better illustrate the present 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 construed as limitations on the present application. DETAILED DESCRIPTION

[0015] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0016] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation 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 indicates 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.

[0017] In addition, it should be noted that, unless otherwise clearly specified 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.

[0018] 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 plate 4, a diverter plate 5, and a cover plate 6.

[0019] Front cover 1 Figure 3 As shown, the cross section is V-shaped with both ends open.

[0020] Tail board 2 Figure 4 As shown, it is connected to the rear opening of the front cover 1. Specifically, the tail plate 2 can be designed to have outward folds on both sides, and the two outward folds are connected to the side walls on both sides of the rear opening of the front cover 1. The tail plate 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 plate 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, and the positions of the cooling holes A, the premixed flow holes B, and the gas flow holes C are staggered in the axial direction.

[0021] Inner cover 3 Figure 5 As shown, the cross section is rectangular or V-shaped, the upper end is open, the lower end is blocked, it is set in the front cover 1, the rear opening is connected to the tail plate 2, and the lower ends of the side walls on both sides have flow holes D. The upper section of the inner cover 3 has a larger size than the lower section, and the upper and lower sections have a smooth transition. The two flow holes D are rectangular.

[0022] 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.

[0023] Divider 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 plate 4, and is located between the two flow holes D.

[0024] 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, and the two secondary premixing chambers G are connected to two rows of premixing outflow holes B.

[0025] 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.

[0026] The double-bend premixing preevaporation type flame stabilizer disclosed in the above embodiment can be radially arranged in the combustion chamber of an aircraft engine during specific application, so that the upper ends of the cooling chamber H and the first-stage premixing chamber E are connected to the outer culvert, the outer culvert airflow is introduced, and the fuel is introduced from the upper end into the first-stage premixing chamber E and the combustion chamber F.

[0027] The external airflow entering the cooling chamber 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 the high-temperature gas from burning on the wall, thereby avoiding structural damage.

[0028] The external airflow entering the first-stage premixing chamber E will be mixed and evaporated along the way with the fuel entering the first-stage premixing chamber E, and then deflected to the second-stage premixing chamber G through two flow holes D, and 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 reflux area formed at the trailing edge of the stabilizer.

[0029] 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 ignition and flame connection of the stabilizer and its stable combustion capabilities, and preventing the fuel from evaporating quickly, easily self-igniting, and causing structural damage and other problems.

[0030] The double-bend premixed preevaporated flame stabilizer disclosed in the above embodiment is a double-bend flame stabilizer that utilizes outer bypass airflow for cooling and premixes and preevaporates with fuel. It can utilize the premixed preevaporation of fuel and outer bypass airflow to increase the oil-gas ratio at the trailing edge of the stabilizer, thereby being able to improve 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 the structural reliability at the right boundary of the aircraft engine and when the intake temperature is high.

[0031] 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 substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A double-baffle premixed preevaporation flame stabilizer, characterized in that: It comprises a front cover (1), a tail plate (2), an inner cover (3), a partition plate (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, is arranged inside the front cover (1), has a rear opening connected to the tail plate (2), and has flow holes (D) at the lower ends of the side walls on both sides; The partition plate (4) is connected to the inner side of the inner cover (3) to divide the inner cover (3) into a primary premixing chamber (E) and a fuel gas chamber (F); the premixing chamber (E) is connected to two flow holes (D), and the fuel gas chamber (F) is connected to multiple rows of fuel 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), and form a secondary premixing chamber (G) between the side walls on both sides of the inner cover (3), and the two secondary premixing chambers (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 holes (B) are located between the two rows of cooling holes (A), and multiple rows of gas flow holes (C) are located between the two rows of premixed flow holes (B), and the positions of the cooling holes (A), the premixed flow holes (B), and the gas flow 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 includes a manifold (5); The flow divider (5) 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).

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