Lubricating oil cooling system of aero-engine

Abstract

The invention provides a lubricating oil cooling system of an aero-engine. A fuel oil booster pump is connected with a conversion valve II and a fuel oil pump I through a temperature sensor II; the fuel pump I is connected with the radiator I; the second fuel pump is connected with the third radiator, the second radiator is connected with the second conversion valve, and the second radiator is connected with the aircraft fuel tank. The bypass valve II is connected with the radiator III in parallel; the bypass valve I is connected with the radiator I in parallel; the one-way valve is connected with the third radiator, the engine is connected with the first temperature sensor and the second radiator, the third bypass valve is connected with the third radiator in parallel, and the first conversion valve and the first temperature sensor are sequentially connected with the engine. The invention has the advantage of effectively solving the problems of damage to parts and components of a lubricating oil system and coking of the lubricating oil caused by over-high temperature of the lubricating oil or high heat dissipation effect of a fuel oil system.

Description

Technical Field

[0001] The invention relates to the field of lubricating oil cooling systems, and in particular to a lubricating oil cooling system for an aircraft engine. Background Art

[0002] The lubricating oil system of an aircraft engine is a closed circulation system. The heat of the lubricating oil system of an aircraft engine mainly comes from the friction heat generated by the bearings and transmission gears, the heat conducted through the structure outside the bearing cavity, and the hot air entering the lubricating oil system. The lubricating oil lubricates and cools the bearings, gears, and contact seals. The operating temperature limit requirement of the lubricating oil is generally not more than 200°C. After high temperature, the lubricating oil system will cause harm to bearings, gears, etc., and cause the problem of high-temperature lubricating oil coking. The present invention will reduce the lubricating oil temperature by setting a radiator in the lubricating oil system and using low-temperature fuel to dissipate the high-temperature lubricating oil after work, so that the operating temperature of the lubricating oil meets the design requirements. Summary of the invention

[0003] The purpose of the present invention is to lower the temperature of the lubricating oil by arranging a radiator in the lubricating oil system and using low-temperature fuel to dissipate the heat of the high-temperature lubricating oil after operation, so that the working temperature of the lubricating oil meets the design requirements.

[0004] The present invention provides an aircraft engine lubricating oil cooling system, which is characterized in that the aircraft engine lubricating oil cooling system includes a fuel boost pump 1, a temperature sensor 2, a conversion valve 3, a fuel pump 4, a fuel pump 5, a radiator 6, a bypass valve 7, a one-way valve 8, an engine 9, a bypass valve 3, a radiator 3 11, a temperature sensor 12, a conversion valve 13, a bypass valve 14, a radiator 15, and an aircraft fuel tank 16.

[0005] Wherein: the fuel boost pump 1 is connected to the conversion valve 2 3 and the fuel pump 1 4 through the temperature sensor 2; the fuel pump 1 4 is connected to the radiator 1 15;

[0006] The fuel pump 2 5 is connected to the radiator 3 11, the radiator 2 6 is connected to the conversion valve 2 3, and the radiator 2 6 is connected to the aircraft fuel tank 16;

[0007] The bypass valve 2 7 is connected in parallel with the radiator 3 11, the bypass valve 1 14 is connected in parallel with the radiator 1 15; the one-way valve 8 is connected with the radiator 3 11,

[0008] The engine 9 is connected to the temperature sensor 1 12 and the radiator 2 6, the bypass valve 3 10 is connected in parallel with the radiator 3 11, and the conversion valve 1 13 and the temperature sensor 1 12 are connected to the engine 9 in sequence.

[0009] The lubricating oil system is provided with a radiator 15, a radiator 2 6 and a radiator 3 11, a bypass valve 1, a bypass valve 2 and a bypass valve 3, a temperature sensor 12, a conversion valve 1 and a one-way valve 8;

[0010] Radiator 1 15 and radiator 3 11 are connected in parallel and then connected in series with radiator 2 6; each radiator uses fuel to dissipate heat from the lubricating oil and preheat the fuel at the same time. A temperature sensor 12 and a conversion valve 1 are provided before the parallel structure of radiator 1 15 and radiator 3 11 and after the fuel booster pump, and a one-way valve 2 is provided after the second parallel sensor.

[0011] When the engine is working normally, one of the parallel radiator 15 and the radiator 3 11 participates in the work, and the radiator will also participate in the work throughout the whole process to perform heat exchange between fuel and lubricating oil.

[0012] When the lubricating oil temperature measured by the temperature sensor 12 exceeds the set value, the radiator 15 and the radiator 3 11 will work together to exchange heat between the fuel and the lubricating oil. When the fuel temperature measured by the temperature sensor 12 exceeds the set value, the radiator 2 6 will work together with a parallel radiator 15 or radiator 3 11, and return the fuel with a high temperature to the aircraft fuel tank 16, and use more initial fuel with a lower temperature to cool the fuel, so that the temperature of the fuel supplied to the fuel system for heat dissipation is lowered, so as to further reduce the lubricating oil temperature.

[0013] The three radiators of the present invention all dissipate heat for the lubricating oil at different times. Meanwhile, a bypass valve is provided on the radiator side branch. When the lubricating oil cavity of the radiator is blocked, the lubricating oil will flow through the bypass valve to ensure that the required lubricating oil is provided to the engine.

[0014] The fuel system is provided with a temperature sensor 2 and a conversion valve 2 3. When the aircraft engine is working normally, the radiator 1 15 performs heat exchange between fuel and lubricating oil, while the lubricating oil flows through the radiator 2 6, but the fuel does not flow through it, and the radiator 3 11 flows through the fuel but does not flow through the lubricating oil and does not participate in the work; a one-way valve 8 is provided behind the radiator 3 11 to prevent the lubricating oil from returning through the radiator 1 15.

[0015] When the lubricating oil temperature measured by temperature sensor 12 exceeds the set value, radiator 1 15 and radiator 3 11 both perform heat exchange between fuel and lubricating oil, while radiator 2 6 has lubricating oil flowing through it and fuel does not flow through it and does not participate in the work.

[0016] When the fuel temperature measured by the temperature sensor 2 exceeds the set value, the radiator 1 15 and the radiator 2 6 both perform heat exchange between the fuel and the lubricating oil, while the fuel flows through the radiator 3 11, and the lubricating oil does not flow through and does not participate in the work.

[0017] Only when the temperatures measured by temperature sensor 1 12 and temperature sensor 2 2 exceed the set values, radiator 1 15, radiator 2 6 and radiator 3 11 all perform heat exchange between fuel and lubricating oil.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] The aircraft engine lubricating oil cooling system described in the present invention is used for aircraft engines where the lubricating oil temperature exceeds the upper working limit of 200°C. Long-term use will cause the lubricating oil to deteriorate and coke, etc., reducing the reliability of the engine. The present invention is a lubricating oil cooling system, in which three radiators are arranged, and each radiator participates in the work at a different time. One radiator 15 is always involved in the work, and the other two radiators are respectively triggered to dissipate the lubricating oil together with the first radiator 15 when the lubricating oil temperature and the fuel temperature exceed the set value, so as to reduce the temperature of the lubricating oil and enable the lubricating oil system to work safely and reliably. The present invention can effectively solve the problems of damage to lubricating oil system components and lubricating oil coking caused by excessively high lubricating oil temperature or high heat dissipation effect of the fuel system. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments:

[0021] Figure 1 This is a schematic diagram of the lubricating oil cooling system;

[0022] In the figure, fuel boost pump 1, temperature sensor 2 2, conversion valve 2 3, fuel pump 1 4, fuel pump 2 5, radiator 2 6, bypass valve 2 7, check valve 8, engine 9, bypass valve 3 10, radiator 3 11, temperature sensor 1 12, conversion valve 1 13, bypass valve 1 14, radiator 1 15, aircraft fuel tank 16. DETAILED DESCRIPTION

[0023] The present invention will be further explained below in conjunction with specific implementation plans, but the present invention is not limited thereto. The structures, proportions, sizes, etc. illustrated in the drawings of the specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the restrictive conditions under which the present invention can be implemented. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0024] The present invention provides an aircraft engine lubricating oil cooling system, which is characterized in that the aircraft engine lubricating oil cooling system includes a fuel boost pump 1, a temperature sensor 2, a conversion valve 3, a fuel pump 4, a fuel pump 5, a radiator 6, a bypass valve 7, a one-way valve 8, an engine 9, a bypass valve 3, a radiator 3 11, a temperature sensor 12, a conversion valve 13, a bypass valve 14, a radiator 15, and an aircraft fuel tank 16.

[0025] Wherein: the fuel boost pump 1 is connected to the conversion valve 2 3 and the fuel pump 1 4 through the temperature sensor 2; the fuel pump 1 4 is connected to the radiator 1 15;

[0026] The fuel pump 2 5 is connected to the radiator 3 11, the radiator 2 6 is connected to the conversion valve 2 3, and the radiator 2 6 is connected to the aircraft fuel tank 16;

[0027] The bypass valve 2 7 is connected in parallel with the radiator 3 11, the bypass valve 1 14 is connected in parallel with the radiator 1 15; the one-way valve 8 is connected with the radiator 3 11,

[0028] The engine 9 is connected to the temperature sensor 1 12 and the radiator 2 6, the bypass valve 3 10 is connected in parallel with the radiator 3 11, and the conversion valve 1 13 and the temperature sensor 1 12 are connected to the engine 9 in sequence.

[0029] The lubricating oil system is provided with a radiator 15, a radiator 2 6 and a radiator 3 11, a bypass valve 1, a bypass valve 2 and a bypass valve 3, a temperature sensor 12, a conversion valve 1 and a one-way valve 8;

[0030] Radiator 1 15 and radiator 3 11 are connected in parallel and then connected in series with radiator 2 6; each radiator uses fuel to dissipate heat from the lubricating oil and preheat the fuel at the same time. A temperature sensor 12 and a conversion valve 1 are provided before the parallel structure of radiator 1 15 and radiator 3 11 and after the fuel booster pump, and a one-way valve 2 is provided after the second parallel sensor.

[0031] When the engine is working normally, one of the parallel radiator 15 and the radiator 3 11 participates in the work, and the radiator will also participate in the work throughout the whole process to perform heat exchange between fuel and lubricating oil.

[0032] When the lubricating oil temperature measured by the temperature sensor 12 exceeds the set value, the radiator 15 and the radiator 3 11 will work together to exchange heat between the fuel and the lubricating oil. When the fuel temperature measured by the temperature sensor 12 exceeds the set value, the radiator 2 6 will work together with a parallel radiator 15 or radiator 3 11, and return the fuel with a high temperature to the aircraft fuel tank 16, and use more initial fuel with a lower temperature to cool the fuel, so that the temperature of the fuel supplied to the fuel system for heat dissipation is lowered, so as to further reduce the lubricating oil temperature.

[0033] The three radiators of the present invention all dissipate heat for the lubricating oil at different times. Meanwhile, a bypass valve is provided on the radiator side branch. When the lubricating oil cavity of the radiator is blocked, the lubricating oil will flow through the bypass valve to ensure that the required lubricating oil is provided to the engine.

[0034] The fuel system is provided with a temperature sensor 2 and a conversion valve 2 3. When the aircraft engine is working normally, the radiator 1 15 performs heat exchange between fuel and lubricating oil, while the lubricating oil flows through the radiator 2 6, but the fuel does not flow through it, and the radiator 3 11 flows through the fuel but does not flow through the lubricating oil and does not participate in the work; a one-way valve 8 is provided behind the radiator 3 11 to prevent the lubricating oil from returning through the radiator 1 15.

[0035] When the lubricating oil temperature measured by temperature sensor 12 exceeds the set value, radiator 1 15 and radiator 3 11 both perform heat exchange between fuel and lubricating oil, while radiator 2 6 has lubricating oil flowing through it and fuel does not flow through it and does not participate in the work.

[0036] When the fuel temperature measured by the temperature sensor 2 exceeds the set value, the radiator 1 15 and the radiator 2 6 both perform heat exchange between the fuel and the lubricating oil, while the fuel flows through the radiator 3 11, and the lubricating oil does not flow through and does not participate in the work.

[0037] Only when the temperatures measured by temperature sensor 1 12 and temperature sensor 2 2 exceed the set values, radiator 1 15, radiator 2 6 and radiator 3 11 all perform heat exchange between fuel and lubricating oil.

[0038] Matters not covered by the present invention are known technologies.

[0039] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft engine oil cooling system, characterized in that: The aircraft engine lubricating oil cooling system comprises a fuel boost pump (1), a second temperature sensor (2), a second conversion valve (3), a fuel pump (4), a second fuel pump (5), a second radiator (6), a second bypass valve (7), a check valve (8), an engine (9), a third bypass valve (10), a third radiator (11), a first temperature sensor (12), a first conversion valve (13), a first bypass valve (14), a first radiator (15), and an aircraft fuel tank (16). Wherein: the fuel boost pump (1) is connected to the conversion valve 2 (3) and the fuel pump 1 (4) through the temperature sensor 2 (2); the fuel pump 1 (4) is connected to the radiator 1 (15); Fuel pump 2 (5) is connected to radiator 3 (11), radiator 2 (6) is connected to conversion valve 2 (3), and radiator 2 (6) is connected to the aircraft fuel tank (16); The bypass valve 2 (7) is connected in parallel with the radiator 3 (11), the bypass valve 1 (14) is connected in parallel with the radiator 1 (15); the one-way valve (8) is connected with the radiator 3 (11), The engine (9) is connected to the temperature sensor 1 (12) and the radiator 2 (6), the bypass valve 3 (10) is connected to the radiator 3 (11) in parallel, and the conversion valve 1 (13) and the temperature sensor 1 (12) are connected to the engine (9) in sequence.

2. The aircraft engine oil cooling system according to claim 1, characterized in that: When the engine (9) is working normally, one of the parallel radiator 1 (15) and the radiator 3 (11) will participate in the work, and the radiator will also participate in the work throughout the whole process to perform heat exchange between fuel and lubricating oil.

3. The aircraft engine oil cooling system according to claim 1, characterized in that: When the lubricating oil temperature measured by temperature sensor 1 (12) exceeds the set value, radiator 1 (15) and radiator 3 (11) start working at the same time to perform heat exchange between fuel and lubricating oil.

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