An adaptive active cooling system and method for an aircraft engine accessory system

Abstract

The application discloses an adaptive active cooling system and method for an aero-engine accessory system, which comprises a liquid storage tank, the liquid storage tank is connected with a heat exchanger to form a liquid supply circulation loop, the heat exchanger is connected with a heating device, a conveying device and the aero-engine accessory system to form a cooling circulation loop; the heat exchanger is connected with the aero-engine accessory system to cool the cooling medium passing through the aero-engine accessory system, the heat exchanger is connected with the heating device, the heating device is connected with the aero-engine accessory system through the conveying device, a first flow control device is arranged on a pipeline between the conveying device and the aero-engine accessory system, and a temperature detection device is arranged on the surface of the aero-engine accessory system; the conveying device, the first flow control device and the temperature detection device are connected with a controller respectively. The application can actively adjust the cooling effect according to real-time working conditions and environmental conditions, can ensure that the best cooling performance can be provided under different working conditions, can adjust the cooling power, effect and efficiency according to requirements, and can avoid excessive cooling or insufficient cooling.

Description

TECHNICAL FIELD

[0001] The present application relates to a cooling system and method of an aircraft, in particular to an adaptive active cooling system and method of an aircraft engine accessory system. BACKGROUND

[0002] The airborne accessories of an aircraft engine are the basis and core of the electronicization, automation, intelligentization and safety of a hypersonic aircraft. The reliability thereof determines the stability and efficiency of the aircraft during flight. Research results of the US Air Force avionics show that the number of electronic components that fail due to excessively high temperature accounts for 55% of the total number of electronic component failures. It can be seen that the surface temperature is an important factor affecting the normal operation of electronic components and indirectly affects the safety and performance of the aircraft. Therefore, effective thermal management of the electronic components in the cabin is an important part of maintaining the normal and efficient operation of the aircraft.

[0003] At present, the thermal protection of the aircraft engine accessory system can be mainly divided into passive thermal protection technology, semi-active thermal protection technology and active thermal protection technology. Passive thermal protection is a method of reducing heat or temperature by using external heat insulation accessories such as thermal insulation materials, which does not require additional energy supply, reduces energy consumption and operating costs, and is generally simple in structure, stable and reliable, and is not prone to failure. However, its control ability is weak, it is difficult to actively adjust the cooling effect, it is easily affected by the external environment, and in addition, the efficiency is relatively low. Semi-active thermal protection is a method of reducing heat or temperature by using external energy or technical means, which has the advantages of high energy efficiency and flexible control. However, this method has high cost, moderate system complexity, and is difficult to maintain, requiring professional technical personnel to operate and maintain, and has many additional devices, such as additional sensors and actuators, which increases the system complexity, and therefore is not commonly used. Active thermal protection is a method of consuming energy to achieve the cooling effect of the target, which can continuously process components with high heat flux. Due to its high temperature control accuracy, high efficiency, strong reliability and strong customizability, it is often used for thermal protection of the aircraft engine accessory system. However, in general, active thermal protection has high energy consumption and requires additional energy to operate, which may increase fuel consumption. SUMMARY

[0004] The purpose of the present application is to provide an adaptive active cooling system for an aircraft engine accessory system that can adjust the cooling medium flow rate to reduce the cooling medium flow rate and energy consumption according to the required cooling medium flow rate of the accessory system.

[0005] The second purpose of the present application is to provide a method for adaptive active cooling of an aircraft engine accessory system using the above system.

[0006] Technical solution: The adaptive active cooling system of the aero-engine accessory system, comprising a liquid storage tank for storing cooling medium, the liquid storage tank is connected with a heat exchanger to form a liquid supply circulation loop, the heat exchanger and the heating device, the conveying device, the aero-engine accessory system form a cooling circulation loop; the heat exchanger is connected with the aero-engine accessory system for cooling the cooling medium passing through the aero-engine accessory system, the heat exchanger is connected with the heating device for heating the cooled cooling medium to reduce the cold damage to the aero-engine accessory system, the heating device is connected with the aero-engine accessory system through the conveying device for conveying the heated cooling medium to the engine accessory system to cool the accessory system to be cooled; the cooling medium circulates between the aero-engine accessory system, the heat exchanger, the heating device and the conveying device; a first flow control device is arranged on the pipeline between the conveying device and the aero-engine accessory system, and a temperature detection device is arranged on the surface of the aero-engine accessory system; the conveying device, the first flow control device and the temperature detection device are connected with the controller respectively; the controller calculates the cooling medium flow required by the aero-engine accessory system according to the temperature detected by the temperature detection device, compares the flow data of the first flow control device, and controls the conveying flow of the conveying device according to the comparison result, so that the data collected by the first flow control device is consistent with the required cooling medium flow.

[0007] Wherein, the heating device includes a heatable buffer tank, the heatable buffer tank includes a buffer tank connected with the heat exchanger for receiving the cooling medium, a heater arranged in the buffer tank for heating the cooling medium entering the buffer tank, a temperature acquisition device for acquiring the temperature of the cooling medium in the buffer tank, the temperature acquisition device is connected with the temperature control module, and the temperature control module is connected with the temperature control cabinet; the temperature control cabinet is connected with the heater; the temperature control cabinet obtains the data of the temperature acquisition device through the temperature control module, and then controls the heat output of the heater; the buffer tank is provided with an overflow port, and the overflow port is communicated with the conveying device for conveying the heated cooling medium.

[0008] Wherein, the heatable buffer tank is at least spaced apart from two between the heat exchanger and the conveying device.

[0009] Wherein, the conveying device includes a conveying pipeline connected with the heating device, a motor and a booster pump arranged on the conveying pipeline for conveying the cooling fluid; the first motor is connected with the first motor power control module, and the first motor power control module is connected with the controller.

[0010] The first flow control device comprises a first flow meter arranged on the pipeline for monitoring the flow of cooling medium, a first valve for adjusting the flow of cooling medium, the first flow meter and the first valve are connected with the controller respectively, and a first flow control module connected with the first flow meter and the first valve respectively; the first flow control module is connected with the controller; the first flow control module collects the first flow meter data and transmits to the controller, and the controller controls the opening degree of the first valve according to the information.

[0011] The pipeline between the inlet of the liquid storage tank and the heat exchanger is provided with a second flow meter and a second valve, a second flow control module connected with the second flow meter and the second valve respectively, and the second flow control module is connected with the controller; the controller calculates the flow of the heat exchange medium that should be transported from the liquid storage tank according to the flow of the cooling medium flowing in the heat exchanger, adjusts the opening and closing degree of the second valve according to the size of the flow, and monitors the flow of the heat exchange medium by using the second flow meter.

[0012] The pipeline between the outlet of the liquid storage tank and the heat exchanger is provided with a second booster pump and a second motor, the second motor is connected with a second motor power control module, and the second motor power control module is connected with the controller; the controller calculates the flow of the heat exchange medium that should be transported from the liquid storage tank according to the flow of the cooling medium flowing in the heat exchanger, and calculates the power required by the second motor according to the size of the flow to adjust it.

[0013] The above system is used for the method of adaptive active cooling of the aero-engine accessory system, the controller calculates the cooling medium flow required by the aero-engine accessory cooling according to the temperature detected by the temperature detection device, compares the flow data collected by the flow control device, controls the delivery flow of the delivery device according to the comparison result, and makes the data collected by the flow control device consistent with the calculated required cooling medium flow.

[0014] The controller is preferably a computer, and the control program of the computer can calculate the cooling medium flow required by the aero-engine accessory system cooling, establish a set of model for comprehensive performance evaluation of the aero-engine accessory system, design the optimal flow path layout for the aero-engine accessory system according to the optimal performance scheme, then the optimal flow path layout further distributes the flow, compares the flow data collected by the flow control device, controls the delivery flow of the delivery device according to the comparison result, and makes the data collected by the flow control device consistent with the calculated required cooling medium flow, so as to achieve the highest efficient flow path layout and flow distribution method.

[0015] The method comprises the following steps:

[0016] (A) connecting the adaptive active cooling system of the aircraft engine accessory system with the aircraft engine accessory system (20) to form a circulation loop;

[0017] (B) adjusting the heating device to set the heating temperature of the cooling medium;

[0018] (C) turning on the heating switch of the heating device;

[0019] (D) connecting each control module to the controller and starting;

[0020] (E) after the heater heats the cooling medium to the specified temperature, turning on the conveying device switch through the controller to start the cooling process;

[0021] (F) after the cooling process of the aircraft engine accessory system is completed, turning off the power switch.

[0022] Advantages: Compared with the prior art, the present application has the following remarkable effects: (1) The adaptive active cooling system of the present application can actively adjust the cooling effect according to the real-time working state and environmental conditions, ensuring that the best cooling performance can be provided under different working conditions, and being more flexible than the traditional fixed cooling system; and the cooling power and effect can be adjusted according to the needs, avoiding the situation of excessive cooling or insufficient cooling, effectively saving energy and improving the energy efficiency ratio; (2) The present application can quickly respond to and adapt to changes in different working conditions, keeping the engine within a stable working temperature range, which is beneficial to improve the stability and reliability of the system; (3) The present application provides more accurate and effective cooling control, and the adaptive active cooling system helps to improve the performance of the engine, prolong the service life of the engine and reduce the maintenance cost; (4) The present application can provide users with more convenient and intelligent control experience, better meeting the needs of users for comfort and operating performance. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is a structural schematic diagram of the adaptive active cooling system of the present application;

[0024] Figure 2 is a schematic diagram of the oil flow path designed by the present application. DETAILED DESCRIPTION

[0025] The present application will be further described in detail below.

[0026] As Figure 1As shown, the present application provides an adaptive active cooling system for an aero-engine accessory system 20, which comprises a liquid storage tank 23 for storing cooling medium, the liquid storage tank 23 is connected with a heat exchanger 19 to form a liquid supply circulation loop, the heat exchanger 19 is connected with a heating device, a conveying device and the aero-engine accessory system 20 to form a cooling circulation loop; the heat exchanger 19 is connected with the aero-engine accessory system 20 for cooling the cooling medium passing through the aero-engine accessory system 20, the heat exchanger 19 is connected with the heating device for heating the cooled cooling medium to reduce the cold damage to the aero-engine accessory system 20, the heating device is connected with the aero-engine accessory system 20 through the conveying device for conveying the heated cooling medium into the aero-engine accessory system 20 to cool the accessory system 20; the cooling medium circulates between the aero-engine accessory system 20, the heat exchanger 19, the heating device and the conveying device; a flow control device is arranged on the pipeline between the conveying device and the aero-engine accessory system 20, and a temperature detection device is arranged on the surface of the aero-engine accessory system 20; the conveying device, the flow control device and the temperature detection device are respectively connected with a controller 18; the controller 18 of the embodiment is a computer; the control program of the controller 18 can calculate the cooling medium flow required for cooling the aero-engine accessory system 20, and establish a model for comprehensive performance evaluation of the aero-engine accessory system 20, design the optimal flow path layout for the aero-engine accessory system 20 according to the optimal performance scheme, then the optimal flow path layout further distributes the flow, and compares the flow data collected by the flow control device, controls the conveying flow of the conveying device according to the comparison result, so that the data collected by the flow control device is consistent with the calculated cooling medium flow required, so as to achieve the highest efficient flow path layout and flow distribution method.

[0027] The heating device comprises a heatable buffer tank, the heatable buffer tank comprises a buffer tank connected with the heat exchanger 19 for receiving the cooling medium, a heater arranged in the buffer tank for heating the cooling medium entering the buffer tank, a temperature acquisition device for acquiring the temperature of the cooling medium in the buffer tank, the temperature acquisition device is connected with a temperature control module, the temperature control module is connected with the temperature control cabinet 7; the temperature control cabinet 7 is connected with the heater; the temperature control cabinet 7 obtains the data of the temperature acquisition device through the temperature control module, and then controls the heat output of the heater; the buffer tank is provided with an overflow port, the overflow port is communicated with the conveying device for conveying the heated cooling medium. The heatable buffer tank of the present application is arranged at least two intervals between the heat exchanger 19 and the conveying device. The heating device of the embodiment comprises a first heatable buffer tank 1 and a second heatable buffer tank 2 connected in sequence, the left end of the first heatable buffer tank 1 is an inlet end, the first heatable buffer tank 1 is connected with the heat exchanger 19, receives the cooled cooling medium, and preliminarily heats the cooling medium, which can play a certain buffering role in the heating process of the cooling medium; the left end of the second heatable buffer tank 2 is connected with the right end of the first heatable buffer tank 1, the second heatable buffer tank 2 heats the cooling medium twice, and after the heating is completed, the cooling medium is conveyed through the motor 3 connected with the right end of the second heatable buffer tank 2. The cooling fluid is heated by electric heating, and a suitable inlet temperature is provided for the active cooling of the aero-engine accessory system 20. After the first heatable buffer tank 1 preliminarily heats the cooling fluid, the cooling fluid flows into the second heatable buffer tank 2 for further heating, a first heater (not shown in the figure) and a first thermometer 8 are arranged in the first heatable buffer tank 1, a second heater (not shown in the figure) and a second thermometer 9 are arranged in the second heatable buffer tank 2, the two thermometers respectively acquire the heating temperature of the fluid in the heatable buffer tank, the first thermometer 8 and the second thermometer 9 are respectively connected with a first heating temperature control module and a second heating temperature control module, the two heating temperature control modules respectively transmit the acquired fluid temperature to the temperature control cabinet 7, the power of the first heater and the second heater is automatically controlled by the program algorithm in the temperature control cabinet 7, so that the heating temperature of the fluid is controlled.

[0028] The conveying device comprises a conveying pipeline connected with the heating device, a first motor 3 and a first booster pump 4 arranged on the conveying pipeline, and the first motor 3 and the first motor power control module 10 are connected, the first motor power control module 10 is connected with a computer.

[0029] The first flow control device comprises a first flow meter 11 arranged on the pipeline for monitoring the flow of the cooling medium, and a first valve 13 for adjusting the flow of the cooling medium, the first flow meter 11 and the first valve 13 are connected with a first flow control module 12 respectively, the first flow control module 12 is connected with a controller 18, the first flow control module collects data of the first flow meter 11 and transmits the data to the controller 18, and the controller 18 controls the opening degree of the first valve 13 according to the information.

[0030] The temperature detection device of the embodiment is a thermocouple 16 arranged on the surface of the aero-engine accessory system 20, the thermocouple 16 monitors and records the temperature of the aero-engine accessory system 20, and transmits the collected temperature signal to a computer through a temperature collection module 17, the computer automatically calculates the minimum lubricating oil flow required for cooling the accessory system 20 by judging the size of the temperature of the accessory system 20, and considering that there is an error in the calculated minimum lubricating oil flow, the computer adjusts the size of the first valve 13 through the first flow control module 12 to change the flow size in the flow path, and through the continuous repetition of this process, the computer continuously receives the data feedback of the temperature of the accessory system 20 and the flow in the flow path, and finally adjusts the flow in the flow path to a suitable value.

[0031] The pipeline between the inlet of the liquid storage tank 23 and the heat exchanger 19 is provided with a second flow meter 24 and a second valve 25, a second flow control module 26 connected with the second flow meter 24 and the second valve 25 respectively, and the second flow control module 26 is connected with the controller 18; the controller 18 calculates the flow of the heat exchange medium that should be delivered from the liquid storage tank 23 according to the flow of the cooling medium in the heat exchanger 19, adjusts the opening and closing degree of the second valve 25 according to the size of the flow, and monitors the flow of the heat exchange medium through the second flow meter 24.

[0032] The pipeline between the outlet of the liquid storage tank 23 and the heat exchanger 19 is provided with a second booster pump 22 and a second motor 21, the second motor 21 is connected with a second motor power control module 27, and the second motor power control module 27 is connected with the controller 18; the controller 18 calculates the flow of the heat exchange medium that should be delivered from the liquid storage tank 23 according to the flow of the cooling medium in the heat exchanger 19, and calculates the power required by the second motor 21 according to the size of the flow to adjust the power.

[0033] When the aero-engine accessory system 20 is adaptively and actively cooled, first, the aero-engine accessory system 20 adaptive active cooling system is connected with the aero-engine accessory system 20 to form a circulating loop, then the temperature control cabinet 7 is adjusted, the heating temperature of the cooling medium is set, the heating switch of the temperature control cabinet 7 is turned on, then each control module is connected to the computer, the computer is turned on, after the first heater and the second heater heat the cooling medium to the specified temperature, the first motor 3 switch is turned on through the computer, the cooling medium is circulated in the flow channel to cool the aero-engine accessory system 20, and after the cooling process of the accessory 20 is completed, all power switches are turned off.

[0034] According to the temperature detected by the temperature detection device, the computer can calculate the cooling medium flow required by the aero-engine accessory system 20, and establish a set of comprehensive performance evaluation model for the aero-engine accessory system 20, and then design the optimal flow path layout for the aero-engine accessory system 20 according to the optimal performance scheme, and then the optimal flow path layout further distributes the flow, and compares with the flow data collected by the flow control device, and controls the delivery flow of the delivery device according to the comparison result, so that the data collected by the flow control device is consistent with the calculated cooling medium flow, so as to achieve the highest efficient flow path layout and flow distribution method.

[0035] As shown in Figure 2 Taking five accessories of a certain type of turbine engine as an example, an evaluation system is established according to four evaluation factors of maximum temperature drop of accessory, oil demand flow, cost and temperature margin, through computer control software calculation and analysis, the optimal flow path layout is obtained, that is, the main path one 35 is divided into two branches, the branch one 33 is placed with turbine accessory one 28, the branch two 34 is placed with turbine accessory five 29 and turbine accessory four 30 in order, then the two branches are gathered into a main path two 36, the main path is connected with turbine accessory three 31 and turbine accessory two 32 in order, at this time, the cooling efficiency of the accessory system is the highest.

Claims

1. An adaptive active cooling system for an aircraft engine accessory system, characterized by, The application relates to an aero-engine accessory system cooling device, which comprises a storage tank (23) for storing cooling medium, a heat exchanger (19) connected with the storage tank (23) to form a cooling circulation loop, a heating device, a conveying device and an aero-engine accessory system (20); the heat exchanger (19) is connected with the aero-engine accessory system (20) to cool the cooling medium passing through the aero-engine accessory system (20), the heat exchanger (19) is connected with the heating device to heat the cooled cooling medium so as to reduce the cold damage to the aero-engine accessory system (20), and the heating device is connected with the aero-engine accessory system (20) through the conveying device to convey the heated cooling medium into the aero-engine accessory system (20) to cool the aero-engine accessory system (20). The cooling medium circulates among the aero-engine accessory system (20), the heat exchanger (19), the heating device and the conveying device; a first flow control device is arranged on the pipeline between the conveying device and the aero-engine accessory system (20), and a temperature detection device is arranged on the surface of the aero-engine accessory system (20); the conveying device, the first flow control device and the temperature detection device are connected with a controller (18) respectively; the controller (18) calculates the cooling medium flow required by the aero-engine accessory system (20) according to the temperature detected by the temperature detection device, compares the flow data of the first flow control device, and controls the conveying flow of the conveying device according to the comparison result, so that the data collected by the first flow control device is consistent with the calculated required cooling medium flow.

2. The adaptive active cooling system for an aeroengine accessory system of claim 1, wherein, The heating device comprises a heatable buffer tank, the heatable buffer tank comprises a buffer tank connected with the heat exchanger (19) to receive the cooling medium, a heater arranged in the buffer tank to heat the cooling medium entering the buffer tank, a temperature acquisition module (17) arranged in the buffer tank to acquire the temperature of the cooling medium in the buffer tank, the temperature acquisition module (17) is connected with a temperature control module, the temperature control module is connected with a temperature control cabinet, the temperature control cabinet is connected with the heater, the temperature control cabinet acquires the data of the temperature acquisition module (17) through the temperature control module, and then controls the heat output of the heater; the buffer tank is provided with an overflow port, and the overflow port is communicated with the conveying device to convey the heated cooling medium.

3. The adaptive active cooling system for an aeroengine accessory system of claim 2, wherein, The heatable buffer tank is arranged at least at two intervals between the heat exchanger (19) and the conveying device.

4. The adaptive active cooling system for a gas turbine engine accessory system of claim 1, wherein, The conveying device comprises a conveying pipeline connected with the heating device, a first motor (3) and a first booster pump (4) arranged on the conveying pipeline; the first motor (3) is connected with a first motor power control module (10), and the first motor power control module (10) is connected with the controller (18).

5. The adaptive active cooling system for a gas turbine engine accessory system of claim 1, wherein, The first flow control device comprises a first flow meter (11) arranged on the pipeline for monitoring the flow of cooling medium, a first valve (13) for adjusting the flow of cooling medium, the first flow meter (11) and the first valve (13) are connected with a controller (18) respectively, a first flow control module (12) collects the data of the first flow meter (11) and transmits the data to the controller (18), the controller (18) controls the opening degree of the first valve (13) according to the information.

6. The adaptive active cooling system for a gas turbine engine accessory system of claim 1, wherein, A second flow meter and a second valve (25) are arranged on the pipeline between the inlet of the liquid storage tank (23) and the heat exchanger (19), a second flow control module (26) connected with the second flow meter (24) and the second valve (25) respectively, the second flow control module (26) is connected with the controller (18), the controller (18) calculates the flow of the heat exchange medium that should be delivered from the liquid storage tank (23) according to the flow of the cooling medium flowing through the heat exchanger (19), adjusts the opening and closing degree of the second valve (25) according to the flow, and monitors the flow of the heat exchange medium by using the second flow meter (24).

7. The adaptive active cooling system for a gas turbine engine accessory system of claim 1, wherein, A second booster pump (22) and a second motor (21) are arranged on the pipeline between the outlet of the liquid storage tank (23) and the heat exchanger (19), the second motor (21) is connected with a second motor power control module (27), the second motor power control module (27) is connected with the controller (18), the controller (18) calculates the flow of the heat exchange medium that should be delivered from the liquid storage tank (23) according to the flow of the cooling medium flowing through the heat exchanger (19), and calculates the power required by the second motor (21) according to the flow, and adjusts the power.

8. A method for adaptive active cooling of an aircraft engine accessory system using the system of claim 1, wherein, The controller (18) calculates the flow of the cooling medium required by the aero-engine accessory system (20) according to the temperature detected by the temperature detection device, compares the flow data collected by the flow control device, controls the delivery flow of the delivery device according to the comparison result, and makes the data collected by the flow control device consistent with the calculated required cooling medium flow.

9. The method for adaptive active cooling of a gas turbine engine accessory system of claim 8, wherein, The controller can calculate the flow of the cooling medium required by the aero-engine accessory system (20), establish a set of models for comprehensive performance evaluation of the aero-engine accessory system (20), design the optimal flow path layout for the aero-engine accessory system (20) according to the optimal performance scheme, then the optimal flow path layout further distributes the flow, compares the flow data collected by the flow control device, controls the delivery flow of the delivery device according to the comparison result, and makes the data collected by the flow control device consistent with the calculated required cooling medium flow, so as to achieve the highest efficient flow path layout and flow distribution method.

10. The method of adaptive active cooling of a gas turbine engine accessory system of claim 8, wherein, Specifically comprising the following steps: (A) connecting the adaptive active cooling system of the aero-engine accessory system with the aero-engine accessory system (20) to form a circulation loop; (B) adjusting the heating device to set the heating temperature of the cooling medium; (C) turning on the heating switch of the heating device; (D) connecting each control module to the controller (18) and starting; (E) after the heater heats the cooling medium to the specified temperature, opening the conveying device switch through the controller to start the cooling process; (F) after the cooling process of the aero-engine accessory system (20) is completed, the power switch is turned off.

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