Multifunctional integrated power generation power device for aero-engine

Abstract

The invention belongs to the field of aero-engines, and discloses a multifunctional integrated power generation power device for an aero-engine, which comprises a transmission shaft, an oil pump set and a generator, the transmission shaft is coaxial with a main shaft of the oil pump set and an inner rotor of the generator, the power source of the transmission shaft is the engine, the transmission shaft is connected with the upper end of the oil pump set, and the lower end of the oil pump set is connected with the generator; the oil pump set is of a cycloid pump structure, and an oil supply port and an oil return port of the oil pump set are both integrated on the side wall of the oil pump set. The functions of accessory power supply, oil supply, oil return, medium cleaning, temperature detection, pressure monitoring, system pressure protection and the like are integrated on the power device, and the power device is driven by the engine to operate. The rotating speed of the power device is adjusted to achieve accessory power supply amount control, medium supply amount control, pumping-back amount control and cleaning in the system, real-time monitoring and alarming on the pressure and temperature of the medium in the pumping-back process and system pressure protection. Compared with a traditional engine fuel and lubricating oil system structure, the functions of system accessory power supply quantity control, oil supply quantity control, oil return quantity control, medium cleaning, temperature detection, pressure monitoring, system pressure protection and the like need to be completed in a split mode, and the power device is small in size and light in weight.

Description

Technical Field

[0001] The invention belongs to the field of aircraft engines and relates to a power generation device, in particular to a multifunctional integrated power generation device for aircraft engines. Background Art

[0002] With the advancement of technology, aviation accessories are developing towards intelligent control and high integration, which significantly reduces the size and weight of the system and improves the system efficiency. However, the functions of power supply, oil medium extraction and transportation, medium cleaning, pressure sensing, temperature sensing, system pressure protection and other functions of the engine fuel and lubricating oil system are completed separately. This has caused the problem of heavy weight and large size of the aircraft engine fuel and lubricating oil system.

[0003] In addition, in high-altitude environments, the aircraft engine fuel and lubricating oil system will experience a large change in the fluid velocity at the oil inlet, causing the steady-state oil inlet environment to become a fast-flow environment, and the direction of fluid movement is different from the direction of the oil inlet, making oil inlet difficult. This results in a large high-altitude efficiency attenuation rate for the aircraft engine fuel and lubricating oil system. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a multifunctional integrated power generation device for aircraft engines, which has high speed and high efficiency and can reduce the volume to The weight is 3kg and it has a low altitude efficiency decay rate at high speed.

[0005] The invention points of the present invention:

[0006] A multifunctional integrated power generation device for an aircraft engine comprises a transmission shaft, an oil pump group and a generator, wherein the transmission shaft is coaxial with the main shaft of the oil pump group and the inner rotor of the generator, the power source of the transmission shaft is the engine, the transmission shaft is connected to the upper end of the oil pump group, and the lower end of the oil pump group is connected to the generator; the oil pump group is a cycloid pump structure, and the oil supply port and the oil return port of the oil pump group are integrated on the side wall of the oil pump group.

[0007] Furthermore, the oil pump group has four oil return ports, which are respectively arranged on the side walls of the oil pump group at different heights and different circumferential positions, and each oil return port is provided with a medium cleaning component.

[0008] Furthermore, the opening direction of the oil return port is the same as the axial direction of the transmission shaft, the medium cleaning component is a cylindrical filter structure, and four medium cleaning components are dispersedly arranged around the oil pump group, and the cylindrical direction of the medium cleaning component is the same as the axial direction of the transmission shaft.

[0009] Furthermore, the oil pump assembly has one oil supply port, which is located at the lowermost end of the oil pump assembly.

[0010] Furthermore, a safety valve is provided at the oil pump assembly; the opening direction of the oil supply port is the same as the axial direction of the transmission shaft, and the opening direction of the safety valve is the same as the axial direction of the transmission shaft.

[0011] Furthermore, the internal pipeline of the oil supply port is connected to an inductive monitoring alarm, which senses the temperature and pressure of the medium inside the power unit and triggers low-temperature and low-pressure and high-temperature and high-pressure alarms.

[0012] Furthermore, the opening of the partition inlet inside the oil pump group is at least 85°, and the opening of the partition outlet inside the oil pump group is at least 70°.

[0013] Furthermore, the pipeline inside the oil pump group is widened, specifically, the inlet flow rate is widened from 7m / s to 3-4m / s.

[0014] Furthermore, the ratio of the depth of the partition oil groove inside the oil pump group to the rotor is 0.8.

[0015] Beneficial effects:

[0016] 1. In order to meet the needs of the current engine fuel and lubricating oil system for multifunctional integration, small size, light weight and high efficiency, this product integrates the functions of accessory power supply, oil supply, oil return, medium cleaning, temperature detection, pressure monitoring, system pressure protection, etc. into the power unit. The engine drives the power unit to run, and adjusts the speed of the power unit to realize the power supply control of the system, the supply control of the medium, the withdrawal control, cleaning, and real-time monitoring and alarm of the pressure and temperature of the medium during withdrawal, and system pressure protection. Compared with the structure of the traditional engine fuel and lubricating oil system, the system's accessory power supply control, oil supply control, oil return control, medium cleaning, temperature detection, pressure monitoring, system pressure protection and other functions need to be completed separately. The power unit is small in size and light in weight.

[0017] 2. The present invention achieves the effect of reducing the high-altitude efficiency attenuation rate by designing the internal baffles, inlet and outlet oil circuits and rotor parameters of the oil pump. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for describing the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative work.

[0019] Figure 1 It is an assembly diagram of a multifunctional integrated high-speed and high-efficiency power generation device for an aircraft engine according to the present invention.

[0020] Among them, 1 is the transmission shaft, 2 is the medium cleaning component, 3 is the oil pump group, 4 is the safety valve, 5 is the generator, 6 is the electric connector, and 7 is the induction monitoring alarm. DETAILED DESCRIPTION

[0021] This section is an embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention. In the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0022] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships based on the orientations or positional relationships in the accompanying 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 case referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implying the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0023] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be interpreted in a broad sense, for example, it can be a fixed connection, a detachable connection or an integrated connection; it can be a mechanical connection or a point connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0024] Embodiment 1:

[0025] A multifunctional integrated power generation device for an aircraft engine comprises a transmission shaft 1, an oil pump group 3 and a generator 7, wherein the transmission shaft 1 is coaxial with the main shaft of the oil pump group 3 and the inner rotor of the generator 7, the power source of the transmission shaft 1 is the engine, the transmission shaft 1 is connected to the upper end of the oil pump group 3, and the lower end of the oil pump group 3 is connected to the generator; the oil pump group 3 is a cycloid pump structure, and the oil supply port and the oil return port of the oil pump group 3 are integrated on the side wall of the oil pump group 3.

[0026] The oil pump assembly 3 has four oil return ports, which are respectively arranged on the side walls of the oil pump assembly 3 at different heights and different circumferential positions, and each oil return port is provided with a medium cleaning component 2 .

[0027] The opening direction of the oil return port is the same as the axial direction of the transmission shaft 1. The medium cleaning component 2 is a cylindrical filter structure. Four medium cleaning components 2 are dispersedly arranged outside the oil pump group 3. The cylindrical direction of the medium cleaning component 2 is the same as the axial direction of the transmission shaft 1.

[0028] The oil pump group 3 has one oil supply port, which is arranged at the lowermost end of the oil pump group 3 .

[0029] A safety valve 5 is provided at the oil pump group 3 ; the opening direction of the oil supply port is the same as the axial direction of the transmission shaft 1 , and the opening direction of the safety valve 5 is the same as the axial direction of the transmission shaft 1 .

[0030] The internal pipeline of the oil supply port is connected with an inductive monitoring alarm 7, which senses the temperature and pressure of the medium inside the power device and triggers low-temperature and low-pressure and high-temperature and high-pressure alarms.

[0031] The opening degree of the partition inlet inside the oil pump group 3 is at least 85°, and the opening degree of the partition outlet inside the oil pump group 3 is at least 70°.

[0032] The pipeline inside the oil pump group 3 is widened, specifically, the inlet flow rate is widened from 7 m / s to 3-4 m / s.

[0033] The ratio of the depth of the partition oil groove inside the oil pump group 3 to the rotor is 0.8.

[0034] Embodiment 2:

[0035] like Figure 1 , Assembly diagram of a multifunctional integrated high-speed and high-efficiency power generation device for aircraft engines, 1 transmission shaft, 2 medium cleaning components, 3 oil pump group, 4 safety valve, 5 generator, 6 electric connector, 7 induction monitoring alarm

[0036] The oil pump group and the generator in the power device adopt a coaxial transmission design, which can realize the adjustment of the medium delivery and withdrawal flow rate and the adjustment of the power generation by adjusting the speed. The engine drives the transmission shaft (1) to rotate and thus drives the power device to operate. By adjusting the transmission speed, the power supply of the accessories in the power device can be adjusted, the supply of the medium can be adjusted, the withdrawal amount can be controlled, cleaned, and the pressure and temperature sensing of the medium during withdrawal, and the system pressure protection can be realized. The medium cleaning component (2) can filter the medium to realize the medium cleaning function. The oil pump group (3) can realize the oil medium withdrawal and delivery. The oil pump group consists of four return oil pumps and one supply oil pump. The safety valve (4) realizes the pressure protection of the system. The generator (5) realizes the power supply to other accessories. The electric connector (6) realizes the connection with other accessories. The temperature and pressure sensing monitoring alarm (7) can realize the pressure and temperature monitoring and alarm during the medium pumping. Through the design of the components in the pump group (diaphragm cavity, rotor, eccentric housing), it can withstand high speeds and work under conditions of different altitudes, thereby realizing oil supply and return and power generation control at different speeds and altitudes.

[0037] This product is a multifunctional integrated high-speed and high-efficiency power generation device for aircraft engines. The engine drives the power device to operate. The power supply to accessories and the amount of oil medium withdrawal and delivery can be controlled by adjusting the speed.

[0038] The generator and oil pump are integrated and connected by bolts to realize the power supply of accessories and the extraction and delivery of oil medium.

[0039] Integrate the system protection function into the power unit and use bolt connections to achieve pressure protection of the engine system.

[0040] The medium cleaning function is integrated into the power unit and a threaded connection is used to realize the cleaning function of the oil medium.

[0041] Integrate the temperature and pressure sensing monitoring alarm into the sensing monitoring alarm to achieve multi-functional integration.

[0042] The induction monitoring alarm is integrated into the power unit using threaded connections to achieve real-time temperature and pressure sensing and alarm functions of the medium.

[0043] The power unit has a high degree of integration, with a volume of □160mm×321mm and a weight of 3kg. It has a small volume and a large flow rate, and the four oil return stages can reach more than 40L / min, and the oil supply stage can reach 25L / min.

[0044] By designing the internal baffle, eccentric housing, oil circuit and rotor of the oil pump, the high-altitude efficiency attenuation rate can be reduced, the pump is resistant to high speeds and can adapt to multiple speeds and multiple altitude conditions.

[0045] Increase the inlet and outlet opening of the partition (increase the inlet opening to more than 85° and the outlet opening to more than 70°)

[0046] Widen the internal pipelines of each level of inlet (from the inlet flow rate of 7m / s to 3-4m / s)

[0047] Rotor width-to-diameter ratio (controlled between 0.16 and 0.18)

[0048] Achieve low altitude efficiency attenuation rate at high speed (13900r / min)

[0049] The depth of the partition oil groove is reduced (the ratio of the oil groove depth to the rotor is 0.8) to reduce the axial volume and reduce the weight without changing the performance.

[0050] The electric connector is connected to the generator by bolts to realize the power supply connection of other accessories.

[0051] The oil pump group and the generator adopt coaxial transmission, which can adjust the speed and simultaneously adjust the medium delivery and withdrawal flow and the power generation.

[0052] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.

Claims

1. A multifunctional integrated power generation device for an aircraft engine, characterized in that: The invention comprises a transmission shaft (1), an oil pump group (3) and a generator (7), wherein the transmission shaft (1) is coaxial with the main shaft of the oil pump group (3) and the inner rotor of the generator (7), the power source of the transmission shaft (1) is an engine, the transmission shaft (1) is connected to the upper end of the oil pump group (3), and the lower end of the oil pump group (3) is connected to the generator; the oil pump group (3) is a cycloid pump structure, and the oil supply port and the oil return port of the oil pump group (3) are integrated on the side wall of the oil pump group (3).

2. A multifunctional integrated power generation device for an aircraft engine according to claim 1, characterized in that: The oil pump group (3) has four oil return ports, which are respectively arranged on the side walls of the oil pump group (3) at different heights and different circumferential positions, and each oil return port is provided with a medium cleaning component (2).

3. The multifunctional integrated power generation device for an aircraft engine according to claim 2, characterized in that: The opening direction of the oil return port is the same as the axial direction of the transmission shaft (1); the medium cleaning component (2) is a cylindrical filter structure; four medium cleaning components (2) are arranged around and dispersed outside the oil pump group (3); and the cylindrical direction of the medium cleaning component (2) is the same as the axial direction of the transmission shaft (1).

4. The multifunctional integrated power generation device for an aircraft engine according to claim 1, characterized in that: The oil pump assembly (3) has one oil supply port, which is arranged at the lowermost end of the oil pump assembly (3).

5. The multifunctional integrated power generation device for an aircraft engine according to claim 4, characterized in that: A safety valve (5) is provided at the oil pump group (3); the opening direction of the oil supply port is the same as the axial direction of the transmission shaft (1), and the opening direction of the safety valve (5) is the same as the axial direction of the transmission shaft (1).

6. The multifunctional integrated power generation device for an aircraft engine according to claim 1, characterized in that: The internal pipeline of the oil supply port is connected to an inductive monitoring alarm (7), which senses the temperature and pressure of the medium inside the power device and triggers low-temperature and low-pressure and high-temperature and high-pressure alarms.

7. The multifunctional integrated power generation device for an aircraft engine according to claim 1, characterized in that: The opening degree of the partition inlet inside the oil pump group (3) is at least 85 degrees, and the opening degree of the partition outlet inside the oil pump group (3) is at least 70 degrees.

8. The multifunctional integrated power generation device for an aircraft engine according to claim 1, characterized in that: The pipeline inside the oil pump group (3) is widened, specifically, the inlet flow rate is widened from 7 m / s to 3-4 m / s.

9. The multifunctional integrated power generation device for an aircraft engine according to claim 1, characterized in that: The ratio of the depth of the partition oil groove inside the oil pump group (3) to the rotor is 0.8.

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