Oil flinger of aero-engine

Abstract

The invention discloses an aero-engine oil flinger, and relates to the field of aero-engine combustion chambers, the aero-engine oil flinger comprises an oil flinger main body, an oil flinger cavity is formed in the oil flinger main body, a plurality of oil outlet holes are formed in the inner side surface of the oil flinger cavity, the oil outlet holes all penetrate through the oil flinger main body, and one side of the oil flinger main body is connected with a central center plate; a throttling hole is formed in the inner side of the central center plate, one side of the throttling hole is matched with the oil throwing cavity in position, a plurality of impellers are connected to the surface of the central center plate and distributed at equal intervals, and an oil throwing disc baffle is connected to the other side of the oil throwing disc body. According to the oil flinger of the aero-engine, the structure of the main body part of the oil flinger is improved, the problems of fuel distribution uniformity, fuel distribution sensitivity and the like of all the oil injection holes can be solved, the core competitiveness of related products is improved, and development of related industrial chains is promoted.

Description

Technical Field

[0001] The present invention relates to the field of aero-engine combustors, and particularly to a fuel slinger for an aero-engine. Background Art

[0002] High rotational speed and compact structure are the prominent features of small aero-engines. Currently, most small aero-engines adopt a structure form of a baffle-type combustor combined with a centrifugal fuel slinger. The fuel slinger is a special form of fuel nozzle, which has the advantages of simple and compact structure, light weight, good atomization performance at high altitude, simple and rapid starting, etc. The fuel slinger is installed on the engine main shaft and rotates at high speed synchronously with the main shaft. Fuel is slung from the small holes at the edge of the fuel slinger to the head of the annular combustor. The fuel is affected by the centrifugal force and interacts with air, breaking and atomizing. For an engine using a fuel slinger fuel nozzle, the combustion efficiency is relatively high, and it also has a cooling effect on the high-speed rotating shaft, and preheats the fuel, which is beneficial to atomization, evaporation, combustion organization and component protection;

[0003] Currently, the structural form of the fuel slinger is mostly of the slinger hole type, the fuel atomization cone angle is relatively small, the fuel discharge amount of each oil hole is not uniform enough, and the breaking and atomization effect needs to be improved, which is not conducive to the mixing of fuel and air in the flame tube;

[0004] Therefore, the present invention proposes a fuel slinger for an aero-engine. Summary of the Invention

[0005] The main purpose of the present invention is to provide a fuel slinger for an aero-engine to solve the problems raised in the background art.

[0006] To achieve the above purpose, the technical solution adopted by the present invention is: a fuel slinger for an aero-engine, including a fuel slinger main body. An oil slinging cavity is arranged inside the fuel slinger main body. A plurality of oil outlet holes are arranged on the inner surface of the oil slinging cavity, and all the plurality of oil outlet holes penetrate through the fuel slinger main body. A central web is connected to one side of the fuel slinger main body. A throttle hole is arranged inside the central web, and one side of the throttle hole is adapted to the position of the oil slinging cavity. A plurality of impellers are connected to the surface of the central web, and all the plurality of impellers are evenly distributed at equal intervals. A fuel slinger baffle is connected to the other side of the fuel slinger main body.

[0007] Preferably, the fuel slinger baffle is snap-connected to the fuel slinger main body, and the central web is welded to the fuel slinger main body, with strong structural advantages.

[0008] Preferably, all the plurality of oil outlet holes are obliquely arranged, and the fuel slinging efficiency is high.

[0009] Preferably, the inner diameter of the throttle hole is smaller than the inner diameter of the oil slinging cavity, effectively forming a throttling effect.

[0010] Preferably, the fuel slinger main body is connected to the engine main shaft.

[0011] The present invention has the following beneficial effects:

[0012] An oil slinger for an aeroengine according to the present invention can enable fuel to obtain relatively high rotational kinetic energy, pressure, etc. by adopting a structure with an impeller, a web plate, a throttle port and an oil outlet. On the basis of a traditional oil slinger, the structure of the main part is improved, the oil supply pressure is reduced, and the use of a high-pressure oil supply device is eliminated. Description of the Drawings

[0013] Figure 1 is a schematic diagram of the overall structure of an oil slinger for an aeroengine according to the present invention;

[0014] Figure 2 is a sectional view taken along the A-A plane of an oil slinger for an aeroengine according to the present invention Figure 1 ;

[0015] Figure 3 is a partial enlarged view at B of an oil slinger for an aeroengine according to the present invention Figure 2 ;

[0016] Figure 4 is a sectional view taken along the E-E plane of an oil slinger for an aeroengine according to the present invention Figure 1 ;

[0017] Figure 5 is a schematic diagram of the bottom structure of an oil slinger for an aeroengine according to the present invention.

[0018] In the figures: 1, oil slinger main body; 2, oil slinger baffle; 3, central web plate; 4, throttle hole; 5, oil slinging cavity; 6, oil outlet hole; 7, impeller. Detailed Embodiments

[0019] To make the above objects, features, and advantages of the present invention more apparent and understandable, the following provides a detailed description of the specific embodiments of the present invention in conjunction with the accompanying drawings. Many specific details are set forth in the following description to facilitate a full understanding of the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without departing from the connotation of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed below. In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention.

[0020] In the present invention, unless otherwise clearly specified and defined, the terms "installed", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] Embodiment 1

[0022] Please refer to Figures 1-5 As shown, the present invention is an oil slinger for an aeroengine, including an oil slinger body 1. An oil slinging chamber 5 is arranged inside the oil slinger body 1. A plurality of oil outlet holes 6 are arranged on the inner surface of the oil slinging chamber 5 (18 groups of oil outlet holes 6 are provided, among which 12 have an oil outlet direction forward and 6 have an oil outlet direction backward). A plurality of oil outlet holes 6 all penetrate through the oil slinger body 1. One side of the oil slinger body 1 is connected to a central web 3. A throttling hole 4 is arranged inside the central web 3. One side of the throttling hole 4 is adapted to the position of the oil slinging chamber 5. A plurality of impellers 7 (6 groups of impellers 7 are provided) are connected to the surface of the central web 3. A plurality of impellers 7 are evenly distributed at equal intervals. The other side of the oil slinger body 1 is connected to an oil slinger baffle 2.

[0023] Among them, the oil slinger baffle 2 is snap-connected to the oil slinger body 1, and the central web 3 is welded to the oil slinger body 1, which is convenient for operation and use; a plurality of oil outlet holes 6 are all obliquely arranged to facilitate the ejection of fuel; the inner diameter of the throttle hole 4 is smaller than the inner diameter of the oil slinging cavity 5 to form a throttling effect; the oil slinger body 1 is connected to the engine main shaft, and the engine use efficiency is improved.

[0024] The present invention relates to an oil slinger for an aeroengine. Six impellers 7 are circumferentially and evenly distributed in the incoming oil direction of the oil slinger. The impellers 7 are connected to the central web 3 and the oil slinger body 1. The oil slinger rotates at a high speed with the rotor shaft. The impellers 7 sling the fuel to the inner wall surface, so that the fuel obtains a high rotational kinetic energy. At the same time, under the action of the central web 3 and the throttle hole 4, the fuel pressure increases, and the high-pressure fuel supply device is omitted; the outer wall of the oil slinger is provided with oil outlet holes 6. Eighteen oil outlet holes 6 are circumferentially and evenly distributed, 12 of which have a forward oil outlet direction and 6 of which have a backward oil outlet direction. The incoming air of the baffle combustion chamber is used to shear the oil mist, further break up the oil droplets, improve the atomization quality, and make the oil-gas mixture uniform.

[0025] Embodiment 2

[0026] The present invention relates to an oil slinger for an aeroengine, including an oil slinger body 1. An oil slinging cavity 5 is arranged inside the oil slinger body 1. A plurality of oil outlet holes 6 are arranged on the inner side surface of the oil slinging cavity 5. The plurality of oil outlet holes 6 all penetrate through the oil slinger body 1. One side of the oil slinger body 1 is connected with a central web 3. A throttle hole 4 is arranged inside the central web 3. One side of the throttle hole 4 is adapted to the position of the oil slinging cavity 5. A plurality of impellers 7 are connected to the surface of the central web 3. The plurality of impellers 7 are evenly distributed at equal intervals. The other side of the oil slinger body 1 is connected with an oil slinger baffle 2. The oil slinger baffle 2 is snap-connected to the oil slinger body 1. The central web 3 is welded to the oil slinger body 1. The plurality of oil outlet holes 6 are all obliquely arranged. The inner diameter of the throttle hole 4 is smaller than the inner diameter of the oil slinging cavity 5. The oil slinger body 1 is connected to the engine main shaft.

[0027] This solution is "not limited to the number of impellers 7", "not limited to the size of the throttle port 4", "not limited to the number and size of the oil outlet ports 6", and "not limited to the distribution mode of the oil outlet ports 6".

[0028] In the description of this specification, the description with reference to terms such as "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0029] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to only the specific embodiments. Obviously, according to the content of this specification, many modifications and variations can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can well understand and utilize the present invention. The present invention is only limited by the claims and their full scope and equivalents.

Claims

1. An oil slinger for an aeroengine, characterized in that: It includes an oil slinger main body (1). An oil slinging cavity (5) is arranged inside the oil slinger main body (1). A plurality of oil outlet holes (6) are arranged on the inner side surface of the oil slinging cavity (5). The plurality of oil outlet holes (6) all penetrate through the oil slinger main body (1). One side of the oil slinger main body (1) is connected with a central web (3). A throttling hole (4) is arranged inside the central web (3). One side of the throttling hole (4) is adapted to the position of the oil slinging cavity (5). A plurality of impellers (7) are connected to the surface of the central web (3). The plurality of impellers (7) are evenly distributed at equal intervals. The other side of the oil slinger main body (1) is connected with an oil slinger baffle (2).

2. The oil slinger of an aeroengine according to claim 1, wherein: The oil slinger baffle (2) is snap-connected to the oil slinger main body (1), and the central web (3) is welded to the oil slinger main body (1).

3. The oil slinger of an aeroengine according to claim 1, characterized in that: The plurality of oil outlet holes (6) are all arranged obliquely.

4. The oil slinger of an aeroengine according to claim 1, characterized in that: The inner diameter of the throttling hole (4) is smaller than the inner diameter of the oil slinging cavity (5).

5. The oil slinger of an aeroengine according to claim 1, wherein: The oil slinger main body (1) is connected to the engine main shaft.

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