Flow dividing device of aero-engine

Abstract

The aero-engine flow dividing device comprises an inner ring, and a plurality of annularly-arranged exhaust holes are symmetrically formed in the inner side wall of the inner ring. The air flow exchange assembly is arranged outside the inner ring, is used for shunting air, and comprises an outer ring I arranged outside the inner ring in a sleeving manner and an outer ring II arranged inside the inner ring in a penetrating manner; the inner side wall of the first outer ring and the inner side wall of the second outer ring are provided with first exhaust holes and second exhaust holes corresponding to the exhaust holes correspondingly, and a plurality of first flow guide plates arranged in an arrayed mode are fixedly arranged between the inner ring and the first outer ring. Compared with the prior art, hot airflow entering the interior can be more comprehensively and fully shunted, the shunting uniformity and sufficiency can be improved, the anti-icing performance can be fully improved in the shunting process, the structure is simple, the production and assembly convenience can be improved, and use is convenient.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aero-engine, especially an aero-engine flow dividing device. BACKGROUND

[0002] The aero-engine is a mechanical mechanism capable of providing thrust and power for the aircraft, which can ensure the safety of the aircraft flight. It is the core power device of the aircraft. The aero-engine flow dividing device is called an aero-engine flow dividing ring. The aero-engine flow dividing ring is a key component for optimizing the performance of the aero-engine, which can improve the heat transfer capacity and uniformity, thereby improving the heat transfer coefficient, and does not need to rely too much on the hot gas of the high-pressure compressor for ice protection, thereby improving the performance of the aero-engine. The flow dividing ring has an outer ring structure and an inner ring structure inside the outer ring structure. The inner ring structure can form an air inlet flow channel, which can further optimize the flow and heat exchange process of the gas.

[0003] According to the search, the Chinese patent with the publication number CN213627789U discloses an aero-engine flow dividing device and an aero-engine. The aero-engine flow dividing device includes a first casing, a second casing, and a leading edge casing. The second casing and the first casing form a tapered air inlet cavity. The leading edge casing is arranged at the outlet of the air inlet cavity. A first flow channel is formed between the leading edge casing and the first casing, and a second flow channel is formed between the leading edge casing and the second casing. The first flow channel and the second flow channel are both in communication with the air inlet cavity. The aero-engine flow dividing device provided by the above technical solution directly forms a first flow channel using the first casing and the leading edge casing, and directly forms a second flow channel using the second casing and the leading edge casing. The above arrangement directly forms a flow channel using the gap between the components, optimizes the flow channel structure, and improves the ice protection performance.

[0004] In the patent, only the first flow channel and the second flow channel can be used to divide the airflow, which cannot fully and comprehensively divide the internal entering hot airflow, is not conducive to improving the uniformity and fullness of the flow division, and is prone to the problem of insufficient flow division leading to insufficient ice protection performance in the flow division process, which is not conducive to improving the safety of the flow dividing device. UTILITY MODEL CONTENTS

[0005] In view of the technical problem in the prior art that only the first flow channel and the second flow channel can be used to divide the airflow, which cannot fully and comprehensively divide the internal entering hot airflow, is not conducive to improving the uniformity and fullness of the flow division, and is prone to the problem of insufficient flow division leading to insufficient ice protection performance in the flow division process, which is not conducive to improving the safety of the flow dividing device, the utility model provides an aero-engine flow dividing device.

[0006] The utility model discloses a technical scheme is: an aeroengine shunt device, including,

[0007] The inner ring is internally symmetrical with a plurality of annularly arranged air dispersing holes;

[0008] The airflow exchange assembly is arranged outside the inner ring, and the airflow exchange assembly is used for shunting gas, and the airflow exchange assembly comprises an outer ring one arranged outside the inner ring and an outer ring two arranged inside the inner ring, the inner side wall of the outer ring one and the inner side wall of the outer ring two are respectively provided with an exhaust hole one and an exhaust hole two corresponding to each air dispersing hole, a plurality of guide plates one are fixedly arranged between the inner ring and the outer ring one, each guide plate one is arranged at intervals from each air dispersing hole and the exhaust hole one, and a plurality of guide plates two are arranged between the inner ring and the outer ring two, and each guide plate two is arranged at intervals from each air dispersing hole and the exhaust hole two.

[0009] Further, the inner part of the outer ring one and the outer ring two is respectively provided with a plurality of gathering holes one and gathering holes two respectively communicating with the exhaust hole one and the exhaust hole two.

[0010] Further, the central part of the inner ring is provided with an air inlet cavity.

[0011] Further, the end part of the outer ring one and the outer ring two is provided with an end plate.

[0012] Further, the end plate and the outer ring one and the outer ring two are respectively fixedly provided with a plurality of annularly arranged baffle plates one and a plurality of annularly arranged baffle plates two, each baffle plate one is arranged at intervals from each gathering hole one, and each baffle plate two is arranged at intervals from each gathering hole two.

[0013] Further, the baffle plate one and the baffle plate two are respectively fixedly provided with a plurality of annularly arranged baffle plates one and a plurality of annularly arranged baffle plates two, each baffle plate one is arranged at intervals from each gathering hole one, and each baffle plate two is arranged at intervals from each gathering hole two.

[0014] Further, the side wall of the outer ring one and the outer ring two is fixedly provided with a back plate fixedly connected with the inner ring.

[0015] The utility model discloses the beneficial effects are:

[0016] The utility model discloses a set up, can realize the more comprehensive and sufficient shunting treatment effect to the hot air flow of inside entering to the setting of air hole, airflow exchange subassembly, exhaust hole no. 1 and exhaust hole no. 2, be favorable to the improvement shunting's evenness and fullness, can more fully improve the anti -icing performance of shunting device in the shunting process, be favorable to the improvement shunting device's functionality and security in use, simple structure is favorable to the improvement production and assembly's convenience. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is the cross section structure schematic diagram of the utility model discloses;

[0018] Figure 2 It is the utility model discloses the Figure 1 The enlarged structure schematic diagram of A in;

[0019] Figure 3 It is the front view structure schematic diagram of the utility model discloses;

[0020] Figure 4 It is the rear view structure schematic diagram of the utility model discloses.

[0021] Marked as in drawing: 1, inner ring;2, air hole;3, airflow exchange subassembly;301, outer ring no. 1;302, outer ring no. 2;303, deflector no. 1;304, deflector no. 2;4, exhaust hole no. 1;5, exhaust hole no. 2;6, gather hole no. 1;7, gather hole no. 2;8, air inlet cavity;9, end plate;10, baffle no. 1;11, baffle no. 2;12, guide hole no. 1;13, guide hole no. 2;14, back plate. SPECIFIC EMBODIMENTS

[0022] In the description of the utility model, it is necessary to explain that the orientation or position relation that the terms "front", "upper", "lower", "left", "right", "vertical", "horizontal" indicate is based on the orientation or position relation shown in the drawing, only for the convenience of describing the utility model and simplifying the description, and not indicate or imply that the device or element indicated must have a particular orientation, construct and operate with a particular orientation, therefore can not be understood as the limitation of the utility model.

[0023] In the description of the utility model, it is necessary to explain that unless another explicit provision and limitation, the terms "mount", "connect", "connect" should be broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected;It can be directly connected, also can be indirectly connected through the intermediate medium, can be the intercommunication of two elements inside.For the ordinary skill of the person skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0024] The following will be combined with the drawings Figures 1-4 Further illustrate the utility model.

[0025] In order to solve the problems existing in the background art, this application proposes the following technical solution: an aero-engine flow splitter.

[0026] The specific technical solution includes an inner ring 1 and an airflow exchange component 3;

[0027] like Figures 1-4 As shown, multiple annularly arranged ventilation holes 2 are symmetrically opened on the inner sidewall of the inner ring 1. The ventilation holes 2 facilitate the entry of gas into the inner ring 1 into the space between the inner ring 1 and the outer ring 1 301 or the outer ring 2 302. The airflow exchange assembly 3 is installed on the outside of the inner ring 1. The airflow exchange assembly 3 is used to divert gas. The airflow exchange assembly 3 includes an outer ring 1 301 sleeved on the outside of the inner ring 1 and an outer ring 2 302 passing through the inside of the inner ring 1. The outer ring 1 301 can protect the outside of the inner ring 1 and can form an airflow cavity with the inner ring 1. The outer ring 2 302 can form an airflow cavity with the inner ring 1. The inner sidewalls of the outer ring 1 301 and the outer ring 2 302 are respectively provided with exhaust holes 1 4 and exhaust holes 2 corresponding to each ventilation hole 2. 5. Exhaust port 1 4 and exhaust port 2 5 can be connected to the air diffuser 2 on both sides respectively to facilitate gas exchange. Multiple guide plates 1 303 are fixedly installed between the inner ring 1 and the outer ring 1 301. The guide plates 1 303 can facilitate the correspondence between each air diffuser 2 on the outer side of the inner ring 1 and each exhaust port 1 4, so as to facilitate the rapid discharge of airflow. Each guide plate 1 303 is spaced apart from each air diffuser 2 and exhaust port 1 4. Multiple guide plates 2 304 are arranged between the inner ring 1 and the outer ring 2 302. The guide plates 2 304 can facilitate the correspondence between each air diffuser 2 on the inner side of the inner ring 1 and each exhaust port 2 5, so as to facilitate the rapid discharge and exchange of gas. Each guide plate 2 304 is spaced apart from each air diffuser 2 and exhaust port 2 5.

[0028] When hot air enters the inner ring 1 through the air inlet chamber 8, the airflow inside the inner ring 1 can enter between the outer ring 301 and the inner ring 1 through various air diffusers 2 and between the outer ring 302 and the inner ring 1. The airflow through the air diffusers 2 outside the inner ring 1 can pass through the inner ring 1, between the two adjacent guide plates 303 and the outer ring 301. After gas exchange, the airflow between the two adjacent guide plates 303 can enter the collecting hole 6 through the exhaust hole 4 and then be discharged from the guide hole 12. The airflow flowing out through the air diffusers 2 inside the inner ring 1 can enter the inner ring 1, between the two adjacent guide plates 304 and the outer ring 302. After heat exchange between the inner ring 1, the two adjacent guide plates 304 and the outer ring 302, the airflow enters the collecting hole 7 through the exhaust hole 5 between the two adjacent guide plates 304. The gas inside the collecting hole 7 can be discharged from the guide hole 13, which can achieve more uniform and sufficient heat exchange.

[0029] likeFigure 2 As shown, the outer ring one 301 and the inner part of the outer ring two 302 are respectively provided with a plurality of gathering holes one 6 and gathering holes two 7 which are communicated with the exhaust hole one 4 and the exhaust hole two 5 respectively, the gathering hole one 6 can drive each exhaust hole one 4 to communicate, when the gas in each exhaust hole one 4 flows out, the gas in each exhaust hole one 4 is gathered in the gathering hole one 6, and then can be discharged through the flow guide hole one 12, the gathering hole two 7 can drive each exhaust hole two 5 to communicate, the gas in each exhaust hole two 5 is gathered in the gathering hole two 7, and the gas in the gathering hole two 7 can be conveniently discharged from the flow guide hole two 13.

[0030] As shown, Figures 1-2 The center part of the inner ring 1 is provided with an air inlet cavity 8, which can conveniently convey gas to the inside of the inner ring 1.

[0031] As shown, Figures 1-3 The end part of the outer ring one 301 and the outer ring two 302 is provided with an end plate 9, which is in a smooth state of circular arc shape, which can facilitate the flow of gas and reduce resistance.

[0032] As shown, Figure 2 The end plate 9 and the outer ring one 301 and the outer ring two 302 are respectively fixedly provided with a plurality of annularly arranged partition plates one 10 and a plurality of annularly arranged partition plates two 11, the partition plate one 10 can drive the end plate 9 and the outer ring one 301 to be fixed, the partition plate two 11 can drive the end plate 9 and the outer ring two 302 to be fixed, each partition plate one 10 is arranged at intervals with each gathering hole one 6, and each partition plate two 11 is arranged at intervals with each gathering hole two 7.

[0033] The partition plate one 10 is arranged at intervals with the gathering hole one 6 and the partition plate two 11 is arranged at intervals with the gathering hole two 7, which can conveniently communicate the gathering hole one 6 with the flow guide hole one 12 and the gathering hole two 7 with the flow guide hole two 13.

[0034] As shown, Figure 2 The adjacent two partition plates one 10 form a flow guide hole one 12 which is communicated with the gathering hole one 6, which can facilitate the gas in the gathering hole one 6 to flow out, and the adjacent two partition plates two 11 form a flow guide hole two 13 which is communicated with the gathering hole two 7, which can facilitate the gas in the gathering hole two 7 to flow out.

[0035] As shown, Figure 4 The side wall of the outer ring one 301 and the outer ring two 302 is fixedly provided with a back plate 14 which is fixedly connected with the inner ring 1, which can connect the inner ring 1, the outer ring one 301 and the outer ring two 302, and can improve the sealing between the outer ring one 301, the outer ring two 302 and the inner ring 1.

[0036] The standard parts used in the utility model can be purchased from the market, the special-shaped parts can be ordered according to the description and the drawings, the specific connection mode of each part adopts the conventional means such as bolts, rivets and welding in the prior art, the machinery, parts and equipment adopt the conventional type in the prior art, the conventional connection mode in the prior art is adopted for circuit connection, and the contents not described in detail in the description belong to the prior art known by the professional technical personnel in the field.

[0037] Although the embodiments of the utility model have been shown and described, the scope of the utility model is defined by the appended claims and their equivalents for those skilled in the art.

Claims

1. An aircraft engine flow splitting device, characterized in that, The utility model relates to a kind of air diffuser, including: Inner ring (1), the inside wall of the inner ring (1) is symmetrically opened multiple annularly arranged air holes (2); Air flow exchange assembly (3), the air flow exchange assembly (3) is installed on the outside of the inner ring (1), the air flow exchange assembly (3) is used to air distribution, the air flow exchange assembly (3) includes outer ring one (301) being installed on the outside of the inner ring (1) and outer ring two (302) being passed in the inside of the inner ring (1), the inside wall of the outer ring one (301) and the outer ring two (302) is opened respectively with each air hole (2) corresponding exhaust hole one (4) and exhaust hole two (5), the inner ring (1) and the outer ring one (301) between fixedly installed multiple arranged guide plates one (303), each guide plate one (303) and each air hole (2) and exhaust hole one (4) are interval arrangement, the inner ring (1) and the outer ring two (302) between arranged multiple guide plates two (304), each guide plate two (304) and each air hole (2) and exhaust hole two (5) are interval arrangement.

2. A flow splitting device for an aeroengine as claimed in claim 1, characterised in that, The inside of the outer ring one (301) and the outer ring two (302) is opened respectively with multiple gathering holes one (6) and gathering holes two (7) being communicated with the exhaust hole one (4) and the exhaust hole two (5).

3. A flow splitting device for an aeroengine as claimed in claim 2, wherein, The center part of the inner ring (1) is opened with air inlet cavity (8).

4. A flow splitting device for an aeroengine according to claim 3, wherein, The end of the outer ring one (301) and the outer ring two (302) is installed with end plate (9).

5. A flow splitting device for an aeroengine as claimed in claim 4, wherein, The end plate (9) and the outer ring one (301) and the outer ring two (302) between fixedly installed multiple annularly arranged baffle one (10) and multiple annularly arranged baffle two (11) respectively, each baffle one (10) and each gathering hole one (6) are interval arrangement, each baffle two (11) and each gathering hole two (7) are interval arrangement.

6. A flow splitting device for an aeroengine as claimed in claim 5, wherein, Between two adjacent baffle one (10), guide hole one (12) being communicated with the gathering hole one (6) is formed, between two adjacent baffle two (11), guide hole two (13) being communicated with the gathering hole two (7) is formed.

7. A flow splitting device for an aeroengine according to claim 6, wherein, The sidewall of the outer ring one (301) and the outer ring two (302) is fixedly installed with back plate (14) being fixedly connected with the inner ring (1).

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