Device for preventing back suction of tail gas of aircraft engine

Abstract

The utility model belongs to the field of aircraft engines, and particularly relates to a device for preventing reverse suction of aircraft engine tail gas. The device comprises a connecting piece, the cross section of the connecting piece is in a V shape, the connecting piece comprises a first connecting part and a second connecting part, and the first connecting part is fixedly installed on an aircraft frame close to an engine tail nozzle; the cross section of the blocking piece is in a V shape, the blocking piece comprises a first blocking piece part and a second blocking piece part, the first blocking piece part is fixedly connected with the second connecting part, and the second blocking piece part extends towards the engine tail nozzle and is used for shielding the space between the aircraft frame and the engine tail nozzle. According to the device for preventing back suction of the tail gas of the aircraft engine, the back suction amount of the tail gas is reduced by reducing the area of the gap between the aircraft structure and the tail nozzle of the engine, meanwhile, due to the fact that the flowing directions of air and ground gas are different, the device belongs to a complex alternating load environment, the structural design strength is high, and replacement is easy.

Description

Technical Field

[0001] The present application belongs to the field of aircraft engines, and in particular relates to a device for preventing exhaust backflow from aircraft engines. Background Art

[0002] When the engine is started on the ground, if there is a favorable wind, the starter may inhale the engine's jet, causing the starter to quit working and the engine to fail to start.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Utility Model Content

[0004] The purpose of the present application is to provide a device for preventing aircraft engine exhaust backflow, so as to solve the problem of engine starting failure caused by the starter sucking the engine jet in the prior art.

[0005] The technical solution of this application is:

[0006] A device for preventing aircraft engine exhaust from back-inhalation, comprising:

[0007] A connecting member, the cross section of which is V-shaped, the connecting member comprising a first connecting portion and a second connecting portion, the first connecting portion being fixedly mounted on an aircraft frame near an engine tail nozzle;

[0008] The baffle has a V-shaped cross-section, and includes a first baffle portion and a second baffle portion. The first baffle portion is fixedly connected to the second connecting portion, and the second baffle portion extends toward the engine tail nozzle. The second baffle portion is used to block the space between the aircraft frame and the engine tail nozzle.

[0009] In at least one embodiment of the present application, a plurality of devices for preventing the back-inhalation of exhaust gas from an aircraft engine are fixedly installed in sections on an aircraft frame near the tail nozzle of the engine.

[0010] In at least one embodiment of the present application, the device for preventing backflow of exhaust gas from an aircraft engine has the same curvature in the length direction as the aircraft frame at which it is located.

[0011] In at least one embodiment of the present application, the first connecting portion is fixedly connected to the aircraft frame by bolts, and the first blocking piece portion is fixedly connected to the second connecting portion by bolts.

[0012] In at least one embodiment of the present application, there is a 15 mm gap between the second baffle portion and the engine tail nozzle.

[0013] The utility model has at least the following beneficial technical effects:

[0014] The device for preventing aircraft engine exhaust backflow in the present application reduces the amount of exhaust backflow by reducing the gap area between the aircraft structure and the engine tail nozzle. At the same time, considering the different gas flow directions in the air and on the ground, which belongs to a complex alternating load environment, the structural design has high strength and is easy to replace. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of a device for preventing exhaust backflow from an aircraft engine according to an embodiment of the present application from one perspective;

[0016] Figure 2 This is a schematic diagram from another perspective of a device for preventing aircraft engine exhaust backflow according to an embodiment of the present application;

[0017] Figure 3 is a schematic diagram of a connector according to an embodiment of the present application;

[0018] Figure 4 It is a schematic diagram of a baffle according to an embodiment of the present application.

[0019] in:

[0020] 1-Connecting piece; 2-Baffle. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0022] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0023] The following is combined with Figures 1 to 4 This application is described in further detail.

[0024] The present application provides a device for preventing aircraft engine exhaust backflow, comprising: a connecting member 1 and a blocking piece 2.

[0025] like Figure 1-2 As shown, the cross-section of the connecting member 1 is V-shaped, and an acute-angle box-shaped structure is preferably adopted. The connecting member 1 includes an integrally formed first connecting portion and a second connecting portion, and the first connecting portion is fixedly mounted on an aircraft frame near the engine tail nozzle; the cross-section of the baffle 2 is V-shaped, and the baffle 2 includes an integrally formed first baffle portion and a second baffle portion, the first baffle portion is fixedly connected to the second connecting portion, and the second baffle portion extends toward the engine tail nozzle, and the second baffle portion is used to shield the space between the aircraft frame and the engine tail nozzle.

[0026] The device for preventing the back-inhalation of exhaust gas from an aircraft engine of the present application, after the baffle 2 is connected to the connecting piece 1, the device for preventing the back-inhalation of exhaust gas from an aircraft engine as a whole forms a triangular cross-section, has high strength, can withstand different alternating loads on the ground and in the air, and realizes the full life design of the aircraft.

[0027] In a preferred embodiment of the present application, the first connecting portion is fixedly connected to the aircraft frame by bolts, and the first blocking piece portion is fixedly connected to the second connecting portion by bolts.

[0028] In a preferred embodiment of the present application, a plurality of devices for preventing the back-inhalation of exhaust gas from an aircraft engine are fixedly installed in sections on an aircraft frame near the tail nozzle of the engine, and the devices for preventing the back-inhalation of exhaust gas from an aircraft engine have the same curvature in the length direction as the aircraft frame at which they are located.

[0029] In the preferred embodiment of the present application, the device for preventing the backflow of aircraft engine exhaust gas can block the space between the aircraft frame and the engine tail nozzle, thereby reducing the gap between the aircraft frame and the engine tail nozzle. In this embodiment, by designing a baffle 2 of a suitable size, a gap of 15 mm is provided between the second baffle portion of each device for preventing the backflow of aircraft engine exhaust gas and the engine tail nozzle, which can greatly reduce the amount of backflow of exhaust gas.

[0030] The device for preventing the backflow of exhaust gas from an aircraft engine of the present application is designed to be composed of two parts, a connector 1 and a baffle 2. The connector 1 and the baffle 2 are fixed on the ground before installation. During installation, the connector 1 only needs to be connected to the aircraft frame by bolts. The connector 1 structure realizes the fixing effect, and the baffle 2 structure realizes the rectification effect. If the gap of the engine is too small or too large due to production error or assembly error, the gap can be adjusted by replacing the baffle 2 structure of the device for preventing the backflow of exhaust gas from an aircraft engine.

[0031] The device for preventing aircraft engine exhaust backflow in the present application has the following advantages:

[0032] (a) It can reduce the gap between the aircraft and the engine tail nozzle, significantly reducing the failure rate of starting failure caused by engine exhaust backflow when the aircraft is started downwind on the ground;

[0033] (b) High reliability. The engine production error and installation error can be adapted by replacing the baffle 2. The replacement is simple, which improves the aircraft reliability.

[0034] It has been verified that the ground start success rate of aircraft equipped with this device to prevent aircraft engine exhaust backflow has been significantly improved.

[0035] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A device for preventing aircraft engine exhaust from back-inhalation, characterized in that: include: A connecting member (1) having a V-shaped cross section, the connecting member (1) comprising a first connecting portion and a second connecting portion, the first connecting portion being fixedly mounted on an aircraft frame near an engine tail nozzle; The baffle (2) has a V-shaped cross section, and comprises a first baffle portion and a second baffle portion, wherein the first baffle portion is fixedly connected to the second connecting portion, and the second baffle portion extends toward the engine tail nozzle, and the second baffle portion is used to shield the space between the aircraft frame and the engine tail nozzle.

2. The device for preventing aircraft engine exhaust backflow according to claim 1, characterized in that: A plurality of devices for preventing aircraft engine exhaust from back-inhalation are fixedly installed in sections on an aircraft frame near the engine tail nozzle.

3. The device for preventing aircraft engine exhaust backflow according to claim 2, characterized in that: The device for preventing the back-inhalation of exhaust gas from an aircraft engine has the same curvature as the aircraft frame at the location in the length direction.

4. The device for preventing aircraft engine exhaust backflow according to claim 1, characterized in that: The first connection portion is fixedly connected to the aircraft frame by bolts, and the first blocking piece portion is fixedly connected to the second connection portion by bolts.

5. The device for preventing aircraft engine exhaust from back-inhalation according to claim 1, characterized in that: There is a 15mm gap between the second baffle portion and the engine tail nozzle.

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