Tilting rotorcraft lubricating system

Abstract

The utility model relates to a tilting rotorcraft lubricating system, belongs to the technical field of aircraft transmission mechanism lubrication, and solves the problems of complex oil path design and low reliability of a tilting rotorcraft in the prior art. The device comprises a fixed lubricating unit and a movable lubricating unit, the fixed lubricating unit is arranged on an input speed reducer (13) and an accessory speed reducer (14), and the movable lubricating unit is arranged on a tilting speed reducer (27); the fixed lubricating unit and the movable lubricating unit do not communicate with each other and operate independently. The fixed lubricating unit and the movable lubricating unit which are independent of each other are adopted, so that movable and static parts do not need to be connected through an oil way, the complexity of the oil way of the lubricating system is reduced, and the overall reliability of the lubricating system is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft transmission mechanism lubrication, in particular to a tiltrotor aircraft lubrication system. Background Art

[0002] The tilt-rotor aircraft is a new type of aircraft based on a new configuration principle. It is a new concept aircraft between helicopters and fixed-wing aircraft. When the rotor tilt system components are in a vertical position, the tilt-rotor aircraft is similar to a twin-rotor horizontal helicopter. It can hover, fly sideways, fly backwards, and take off and land vertically, eliminating the need for a runway. When the rotor tilt system components are in a horizontal position, the tilt-rotor aircraft is equivalent to a fixed-wing aircraft, capable of high-speed long-distance flight and increasing the flight envelope. Its excellent performance has attracted the attention of various experts in the military and civil aviation fields. Based on its configuration principle, its transmission system should also have two modes during flight, in which the tilt reducer can move between a horizontal position and a vertical position. This movement poses a great challenge to the lubrication of its transmission system.

[0003] The current lubrication solution for tiltrotor aircraft uses only one lubrication oil circuit to lubricate the entire aircraft transmission system, and there is a supply and return oil circuit between the moving and static components. The oil circuit design is complex and there is a great risk of reliability. In addition, due to the complex structure between the moving and static components, the reliability of the lubrication system is reduced. Utility Model Content

[0004] In view of the above analysis, an embodiment of the utility model aims to provide a tiltrotor aircraft lubrication system to solve the problems of complex oil circuit design and low reliability of the tiltrotor aircraft.

[0005] On the one hand, the utility model provides a lubrication system for a tiltrotor aircraft, comprising a fixed lubrication unit and a moving lubrication unit, wherein the fixed lubrication unit is arranged on an input reducer and an accessory reducer, and the moving lubrication unit is arranged on the tilt reducer; the fixed lubrication unit and the moving lubrication unit are not connected to each other and operate independently;

[0006] The fixed lubrication unit includes a first oil tank, a first oil supply pipeline and an input reducer oil return pipeline;

[0007] The motion lubrication unit comprises a second oil tank, a third oil tank and a second oil supply pipeline;

[0008] The input end of the second oil supply pipeline is communicated with the oil circuits of the second oil tank and the third oil tank respectively, and the output end of the second oil supply pipeline is communicated with the oil inlet of the tilting reducer.

[0009] Furthermore, the first oil tank is fixedly connected to the accessory reducer, the input end of the first oil supply pipeline is connected to the first oil tank, and the output end of the first oil supply pipeline is connected to the input reducer and the accessory reducer respectively.

[0010] Furthermore, a coarse oil filter and an oil supply pump are provided at the input end of the first oil supply pipeline.

[0011] Furthermore, the second oil tank and the third oil tank are both disposed within the housing of the tilting reducer.

[0012] Furthermore, the second oil tank is located at the lowest point when the tilt reducer is in a vertical position, and the third oil tank is located at the lowest point when the tilt reducer is in a horizontal position.

[0013] Furthermore, the second oil tank and the third oil tank are connected via a casting oil passage.

[0014] Furthermore, a magnetic chip detector and an alarm light are provided at the bottom of the second oil tank and the third oil tank.

[0015] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0016] 1) The utility model provides two independent fixed lubrication units and a moving lubrication unit, so that there is no need for oil circuit connection between the moving and static parts, which greatly reduces the complexity of the oil circuit of the lubrication system and improves the overall reliability of the lubrication system.

[0017] 2) In the utility model, by arranging two oil tanks in the motion lubrication unit, the internal circulation of lubricating oil can be realized in both operating states of the tiltrotor reducer, thereby meeting the lubrication requirements of the tiltrotor aircraft in both flight states, and can monitor various pressures, temperatures and wear conditions during the operation of the transmission system, thereby extending the service life of the transmission system.

[0018] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can become obvious from the description, or can be understood by implementing the present invention. The purpose and other advantages of the present invention can be achieved and obtained through the contents specifically pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings are only used for the purpose of illustrating specific embodiments and are not to be considered as limiting the present invention. In the entire drawings, the same reference symbols represent the same components.

[0020] Figure 1This is a schematic diagram of the principle of a lubrication system for a tiltrotor aircraft of the utility model;

[0021] Figure 2 It is a structural schematic diagram of the transmission system of the tilt-rotor aircraft of the utility model;

[0022] Figure 3 It is a structural schematic diagram of the arrangement positions of the second oil tank and the third oil tank in the utility model;

[0023] Figure 4 It is a structural schematic diagram of the first oil supply pipeline, the input reducer and the accessory reducer in the utility model;

[0024] Figure 5 It is a structural schematic diagram of the second oil tank and the third oil tank and the connecting pipeline in the utility model;

[0025] Figure 6 For the utility model Figure 4 A partial enlargement of the upper left part of .

[0026] Reference numerals:

[0027] 1, 12, 15, 16-coarse oil filter; 11, 25-magnetic chip detector and warning light; 2, 17-oil supply pump; 3, 18-pressure regulating valve; 4, 19-fine oil filter; 5, 20-bypass valve; 6, 21-lubricating oil radiator; 7, 22-bypass valve; 8, 23-temperature sensor and indicator; 9, 24-pressure sensor and indicator; 10-return oil pump; 13-input reducer; 14-accessory reducer; 27-tilting reducer; 28-second oil tank; 29-third oil tank. DETAILED DESCRIPTION

[0028] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0029] Example 1

[0030] A specific embodiment of the utility model is as follows Figure 1 , Figure 2 and Figure 3 As shown, a tiltrotor aircraft lubrication system is disclosed.

[0031] See also Figure 2The conventional tilt-rotor transmission system includes an input reducer 13, an accessory reducer 14, and a tilt reducer 27. The input reducer 13 and the accessory reducer 14 maintain a constant relative position with the aircraft body during the operation of the aircraft, and the tilt reducer 27 has two relative position relationships with the aircraft body depending on the operating state of the aircraft, namely, fixed-wing mode and helicopter mode.

[0032] The utility model relates to a tiltrotor aircraft lubrication system, comprising a fixed lubrication unit arranged on an input reducer 13 and an accessory reducer 14, and a moving lubrication unit arranged on a tilt reducer 27. The fixed lubrication unit and the moving lubrication unit are not connected to each other and operate independently.

[0033] See also Figure 1 and Figure 4 The fixed lubrication unit includes a first oil tank, a first oil supply pipeline and an input reducer oil return pipeline. The first oil tank is fixedly connected to the accessory reducer 14, the input end of the first oil supply pipeline is connected to the first oil tank, and the output end is connected to the input reducer 13 and the accessory reducer 14 respectively. The input end of the first oil supply pipeline is provided with a coarse oil filter 1 and an oil supply pump 2 to provide lubricating oil to the input reducer 13 and the accessory reducer 14.

[0034] The first oil tank is fixedly connected to the accessory reducer 14 , and the bottom of the box body of the accessory reducer 14 may constitute the first oil tank, or a first oil tank may be provided at the bottom of the accessory reducer 14 .

[0035] The oil supply pump 2 is connected in parallel with a pressure regulating valve 3 , and the pressure regulating valve 3 can adjust the oil supply pressure of the oil supply pump 2 .

[0036] Furthermore, a fine oil filter 4, a pressure sensor 8 and a temperature sensor 9 are also provided in the first oil supply pipeline. In the first oil supply pipeline, the lubricating oil first passes through the coarse oil filter 1 provided in the accessory reducer 14, filters out impurities in the oil and enters the oil supply pump 2, then passes through the fine oil filter 4, and enters each nozzle of the input reducer 13 and the accessory reducer 14 for lubrication after being monitored by the pressure sensor 8 and the temperature sensor 9.

[0037] The fine oil filter 4 is connected in parallel with a bypass valve 5. When the fine oil filter 4 is clogged, the bypass valve 5 can be opened to allow normal flow of the oil circuit.

[0038] Furthermore, a lubricating oil radiator 6 is also provided in the first oil supply pipeline. The lubricating oil enters the lubricating oil radiator 6 after passing through the fine oil filter 4. The cooled lubricating oil enters the various nozzles of the input reducer 13 and the accessory reducer 14 for lubrication after being monitored by the pressure sensor 8 and the temperature sensor 9.

[0039] The lubricating oil radiator 6 is connected in parallel with a bypass valve 7. When the lubricating oil temperature is higher than 70 degrees, the bypass valve 7 is closed, and the lubricating oil is cooled through the lubricating oil radiator 6; when the lubricating oil temperature is lower than 70 degrees, the bypass valve 7 is opened, and the lubricating oil does not pass through the lubricating oil radiator 6.

[0040] The input end of the input reducer oil return pipeline is connected to the bottom of the input reducer 13, and a coarse oil filter 12 is provided at the input end. An oil return pump 10 is provided in the input reducer oil return pipeline for pumping the lubricating oil in the input reducer 13 back to the first oil tank.

[0041] In the oil return line of the input reducer, the lubricating oil cools and lubricates the friction pairs, passes through the coarse oil filter 12 arranged in the input reducer 13, and returns the oil through the return oil pump 10 to enter the first oil tank in the accessory reducer 14. The lubricating oil in the accessory reducer 14 directly flows into the first oil tank due to gravity.

[0042] At the same time, the first oil supply pipeline is connected between the input reducer 13 and the accessory reducer 14 as shown in FIG. Figure 4 As shown, the local enlarged picture is as follows Figure 6 As shown, the two reducers are connected by an oil guide sleeve assembly 30 for oil circuit communication, and are sealed by two O-rings on the oil guide sleeve assembly 30 .

[0043] Furthermore, a magnetic chip detector and an alarm light 11 are provided at the bottom of the first oil tank for monitoring magnetic foreign matter in the lubricating oil in the accessory reducer 14 .

[0044] See also Figure 1 , Figure 3 as well as Figure 5 The motion lubrication unit includes a second oil tank 28, a third oil tank 29 and a second oil supply pipeline. The second oil tank 28 and the third oil tank 29 are both arranged in the housing of the tilting reducer 27. Figure 3 The second oil tank 28 is located at the lowest point when the tilt reducer 27 is in the helicopter state, and the third oil tank 29 is located at the lowest point when the tilt reducer 27 is in the fixed-wing state.

[0045] See also Figure 5 The second oil tank 28 and the third oil tank 29 are connected through the casting oil passage, so that the lubricating oil of the tilting reducer 27 will flow into one of the oil tanks under the action of gravity in both modes.

[0046] The second oil supply pipeline is connected to the second oil tank 28 and the third oil tank 29 respectively, and coarse oil filters 15 and 16 are respectively provided at the connecting ports.

[0047] Similar to the first oil supply pipeline, the second oil supply pipeline is sequentially provided with an oil supply pump 17, a fine oil filter 19, a lubricating oil radiator 21, a temperature sensor and an indicator 23, and a pressure sensor and an indicator 24. Similarly, the oil supply pump 17 is connected in parallel with a pressure regulating valve 18, the fine oil filter 19 is connected in parallel with a bypass valve 20, and the lubricating oil radiator 21 is connected in parallel with a bypass valve 22. The working process of the oil supply circuit is consistent with that of the fixed lubrication unit oil supply circuit, and will not be described in detail.

[0048] Furthermore, magnetic chip detectors and warning lights 25 and 26 are respectively provided at the bottom of the second oil tank 28 and the third oil tank 29 to monitor magnetic foreign matter in the lubricating oil of the tilting reducer 27 .

[0049] Compared with the prior art, the tiltrotor aircraft lubrication system provided by this embodiment has a simpler structure, is easy to maintain, has a small space requirement, and greatly reduces costs due to the reduced requirements on the performance of the lubricating oil pump.

[0050] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed in the present invention should be included in the protection scope of the present invention.

Claims

1. A tiltrotor aircraft lubrication system, characterized in that: It comprises a fixed lubrication unit and a moving lubrication unit, wherein the fixed lubrication unit is arranged on an input reducer (13) and an accessory reducer (14), and the moving lubrication unit is arranged on a tilting reducer (27); the fixed lubrication unit and the moving lubrication unit are not connected to each other and operate independently; The fixed lubrication unit includes a first oil tank, a first oil supply pipeline and an input reducer oil return pipeline; The motion lubrication unit comprises a second oil tank (28), a third oil tank (29) and a second oil supply pipeline; The input end of the second oil supply pipeline is communicated with the oil circuits of the second oil tank (28) and the third oil tank (29) respectively, and the output end of the second oil supply pipeline is communicated with the oil inlet of the tilting reducer (27).

2. A tiltrotor aircraft lubrication system according to claim 1, characterized in that: The first oil tank is fixedly connected to the accessory reducer (14), the input end of the first oil supply pipeline is connected to the first oil tank, and the output end of the first oil supply pipeline is respectively connected to the input reducer (13) and the accessory reducer (14).

3. A tiltrotor aircraft lubrication system according to claim 1 or 2, characterized in that: The input end of the first oil supply pipeline is provided with a coarse oil filter (1) and an oil supply pump (2).

4. A tiltrotor aircraft lubrication system according to claim 1, characterized in that: The second oil tank (28) and the third oil tank (29) are both arranged inside the housing of the tilting speed reducer (27).

5. A tiltrotor aircraft lubrication system according to claim 4, characterized in that: The second oil tank (28) is located at the lowest point when the tilt reducer (27) is in a vertical position, and the third oil tank (29) is located at the lowest point when the tilt reducer (27) is in a horizontal position.

6. A tiltrotor aircraft lubrication system according to any one of claims 1, 4-5, characterized in that: The second oil tank (28) and the third oil tank (29) are connected via a casting oil passage.

7. A tiltrotor aircraft lubrication system according to claim 1, characterized in that: A magnetic chip detector and an alarm light are arranged at the bottom of the second oil tank (28) and the third oil tank (29).

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