Jet pre-cooling water supply anti-freezing design architecture with uniform temperature measurement

Abstract

The application belongs to the technical field of aero-engines, and particularly relates to a jet pre-cooling water supply anti-freezing design architecture with uniform temperature measurement. The jet pre-cooling water supply adopts an anti-icing control accessory and an anti-freezing electromagnetic valve. Air from the anti-icing control accessory is used to externally blow the accessories of the jet pre-cooling control device to prevent surface icing. After the jet pre-cooling stops working, the anti-freezing control accessory is used to guide air from the three-zone outlet of the jet pre-cooling control device to the jet pre-cooling nozzle. Before entering a low-temperature environment, the water stored in the pipeline is blown away in advance, so as to prevent the water stored in the pipeline from freezing. Not only is the risk of freezing during flight reduced, but also the requirements for the storage and maintenance of the troops after landing are simplified, the use range of the jet pre-cooling assembly troops is expanded, and the aircraft can still fly safely and highly maneuverably under extremely cold and northern conditions.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a jet precooling water supply antifreeze design architecture with uniform temperature measurement. Background Technology

[0002] In recent years, a great deal of research has been carried out both domestically and internationally on jet precooling expansion envelopes for turbine engines. This involves adding a water spray precooling device to the air intake, injecting atomized liquid water into the air intake, and reducing the total temperature at the engine inlet through the principle of water vaporization and heat absorption. This increases the aircraft's flight speed without changing the geometric, pressure, temperature, and speed limits of the turbine engine.

[0003] To cope with the problem of high-temperature incoming flow, hypersonic aircraft turbine engines need to use jet precooling technology to expand the envelope. The success or failure of the jet precooling system directly determines the engine's ability to expand the envelope. To ensure the normal operation of jet precooling, the design of the jet precooling control system is one of the core key technologies of aerospace engines.

[0004] Hypersonic aircraft operate in low-temperature environments, and the water medium used for jet precooling will freeze below 0°C, causing pipe blockages and bursts. This not only affects the jet precooling function but also poses safety hazards.

[0005] Therefore, the design of a jet precooling water supply antifreeze architecture with uniform temperature measurement is essential. Summary of the Invention

[0006] To address the aforementioned problems, this application provides a jet precooling water supply antifreeze design architecture with uniform temperature measurement, characterized by comprising:

[0007] Water source;

[0008] Water pump; pumps water from the water source to the jet precooling control device;

[0009] The jet precooling control device has a metering valve, and a sensing device connected to the jet precooling controller is installed on the metering valve. The sensing device senses the working parameters of the metering valve.

[0010] The jet pre-cooling injection device sprays water from the jet pre-cooling control device onto the air intake duct;

[0011] The jet precooling controller generates a control current for controlling the metering valve and a control current for controlling the water pump based on the sensing device of the metering valve and the sensing device installed at the engine inlet.

[0012] The anti-icing module includes an anti-icing control accessory, which introduces engine bleed air into the jet pre-cooling injection device and blows anti-icing air onto the icing location of the jet pre-cooling injection device.

[0013] The antifreeze module includes an antifreeze solenoid valve, which purges the easily frozen pipelines with gas from the aircraft gas cylinder.

[0014] The sensor at the engine inlet is installed at the same axial position as the intake manifold.

[0015] The sensing devices imported into the engine include: a set of waterproof imported total temperature sensors, two sets of traditional imported total temperature sensors, and a set of pressure sensors;

[0016] Each set of waterproof inlet total temperature sensors includes two sensors, which are symmetrically distributed along the center of the inlet cross section.

[0017] Each set of traditional imported total temperature sensors includes two sensors, and each set of traditional waterproof imported total temperature sensors is symmetrically distributed along the center of the inlet cross section.

[0018] Each pressure sensor group consists of two sensors, and the pressure sensors in each group are symmetrically distributed along the center of the inlet cross section.

[0019] Traditional imported total temperature sensors are located on both sides of waterproof imported total temperature sensors.

[0020] Preferably, the angle between the axis of the conventional imported total temperature sensor passing through the center of the inlet section and the axis of the waterproof imported total temperature sensor passing through the center of the inlet section are the same.

[0021] Preferably, the angle between the axis of the waterproof inlet total temperature sensor passing through the center of the inlet cross-section and the vertical axis of the inlet cross-section in the counterclockwise direction is 45 degrees; the included angle is 15 degrees.

[0022] Preferably, the water pump includes: an aircraft pump driven by an electric motor, a high-pressure water pump for increasing water pressure, and a water filter located between the aircraft pump and the high-pressure water pump.

[0023] Preferably, the metering valve includes a first-zone metering valve, a third-zone metering valve, and a third-zone metering valve that run in parallel; the first-zone metering valve, the first-zone metering valve, and the third-zone metering valve supply water to the jet precooling injection device individually or simultaneously.

[0024] Preferably, the metering valve sensing device includes a displacement sensor for measuring the opening degree of the metering valve and a pressure sensor for measuring the outlet pressure of the metering valve.

[0025] Preferably, the sensing device at the engine inlet includes a temperature sensor and a pressure sensor box circumferentially mounted at the engine inlet.

[0026] Preferably, the jet precooling controller is connected to a monitoring system, which is used to display the working status of the jet precooling controller.

[0027] The advantages of this application include: By evenly distributing traditional imported total temperature sensors on both sides of the waterproof imported total temperature sensor, it can maximize proximity to the same temperature measurement point, providing a more accurate reflection of the temperature at the measurement location. Utilizing a dissimilar redundancy sensor allows for the acquisition of the engine inlet total temperature sensor time constant under actual installed conditions, resolving the difference in time constant between wind tunnel testing and air jet pre-cooling conditions. Furthermore, the dissimilar redundancy sensor enables compensation for rapidly changing signals over a large range, avoiding undercompensation and overcompensation issues caused by bandpass filtering from a single sensor.

[0028] The true engine inlet temperature cannot be obtained under the pre-cooling state of the jet, so a single sensor solution cannot accurately identify the time constant of the inlet total temperature sensor. This invention introduces a method of 6 non-similar redundancy temperature sensors and 2 pressure sensors, which can solve the problem of the inability to obtain the true time constant.

[0029] Since the airflow field inside the intake duct is constantly changing, circumferentially distributing the inlet total temperature sensor and pressure sensor can reflect the temperature and pressure at different locations inside the intake duct, thus obtaining more accurate measurement results.

[0030] This application employs anti-icing control accessories and anti-freezing solenoid valves for jet precooling water supply. The anti-icing control accessories use bleed air to externally purge the jet precooling control device and other accessories to prevent surface icing. After jet precooling stops working, the anti-freezing control accessories use bleed air to purge the water in the pipeline from the outlet of the three zones of the jet precooling control device to the jet precooling nozzle. Before entering the low-temperature environment, the water in the pipeline is purged in advance, thereby preventing the water in the pipeline from freezing. This not only reduces the risk of freezing during flight but also simplifies the storage and maintenance requirements for troops after landing. It expands the scope of domestic jet precooling applications that can be equipped with troops, allowing aircraft to continue to fly safely and with high maneuverability even in extremely cold and northern conditions. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of a preferred embodiment of the jet precooling water supply antifreeze architecture of this application;

[0032] Figure 2 This is a schematic diagram of the distribution of imported total temperature sensors. Detailed Implementation

[0033] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0034] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0035] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0036] like Figure 1 As shown, to solve the above problems, this application provides a jet precooling water supply antifreeze design architecture with uniform temperature measurement, including:

[0037] Water source;

[0038] Water pump; pumps water from the water source to the jet precooling control device;

[0039] The jet precooling control device has a metering valve, and a sensing device connected to the jet precooling controller is installed on the metering valve. The sensing device senses the working parameters of the metering valve.

[0040] The jet pre-cooling injection device sprays water from the jet pre-cooling control device onto the air intake duct;

[0041] The jet precooling controller generates a control current for controlling the metering valve and a control current for controlling the water pump based on the sensing device of the metering valve and the sensing device installed at the engine inlet.

[0042] The anti-icing module includes an anti-icing control accessory, which introduces engine bleed air into the jet pre-cooling injection device and blows anti-icing air onto the icing location of the jet pre-cooling injection device.

[0043] The antifreeze module includes an antifreeze solenoid valve that purges the easily frozen pipeline with gas from the aircraft gas cylinder; the metering valves include three parallel metering valves: a first-zone metering valve, a third-zone metering valve, and a third-zone metering valve; the first-zone metering valve, the third-zone metering valve, and the third-zone metering valve supply water to the jet precooling injection device individually or simultaneously; the metering valve sensing devices include a displacement sensor for measuring the opening degree of the metering valve and a pressure sensor for measuring the outlet pressure of the metering valve.

[0044] The sensing devices at the engine inlet include a temperature sensor and a pressure sensor box that are circumferentially mounted at the engine inlet.

[0045] The jet precooling controller is connected to a monitoring system, which displays the working status of the jet precooling controller.

[0046] Based on the above-mentioned uniform temperature measurement jet precooling water supply antifreeze design architecture, a jet precooling smooth control method is implemented.

[0047] Step S1: Calculate the expected value T2_Dem of the engine inlet total temperature based on the aircraft Mach number.

[0048] Step S2: The deviation value Delta_T2 is obtained by subtracting the expected value T2_Dem from the total inlet temperature T2 collected by the engine inlet sensor.

[0049] Step S3: Calculate the target water flow rate Ww_dem based on the deviation value Delta_T2;

[0050] Step S4: Divide the target water flow rate Ww_dem into multiple zone flow rates, and supply water to multiple identical water supply zones according to the zone flow rates;

[0051] In step S4, the specific method for supplying water to the water supply zone according to the zone flow rate includes:

[0052] Step S41: The difference between the zone flow rate and the feedback value of the first sensor at the outlet is used to obtain the mid-loop control deviation;

[0053] Step S42: Calculate the middle loop control target by using the PID algorithm to obtain the middle loop control deviation; calculate the difference between the middle loop control target and the feedback value of the second sensor at the outlet to obtain the inner loop control deviation; calculate the inner loop control target by using the PID algorithm to obtain the inner loop control deviation.

[0054] Step S43: Control the current input I of the electro-hydraulic servo valve through the inner loop control target, and control the opening of the outlet metering valve through the current input I, thereby controlling the outlet water flow.

[0055] The sensor at the engine inlet is installed at the same axial position as the intake manifold.

[0056] The sensing devices imported into the engine include: a set of waterproof imported total temperature sensors, two sets of traditional imported total temperature sensors, and a set of pressure sensors;

[0057] Each set of waterproof inlet total temperature sensors includes two sensors, which are symmetrically distributed along the center of the inlet cross section.

[0058] Each set of traditional imported total temperature sensors includes two sensors, and each set of traditional waterproof imported total temperature sensors is symmetrically distributed along the center of the inlet cross section.

[0059] Each pressure sensor group consists of two sensors, and the pressure sensors in each group are symmetrically distributed along the center of the inlet cross section.

[0060] Traditional imported total temperature sensors are located on both sides of waterproof imported total temperature sensors.

[0061] Preferably, the angle between the axis of the conventional imported total temperature sensor passing through the center of the inlet section and the axis of the waterproof imported total temperature sensor passing through the center of the inlet section are the same.

[0062] Preferably, the angle between the axis of the waterproof inlet total temperature sensor passing through the center of the inlet cross-section and the vertical axis of the inlet cross-section in the counterclockwise direction is 45 degrees; the included angle is 15 degrees.

[0063] The principle of sensor placement is:

[0064] Based on the requirement for uniformity of outlet temperature distribution, under the condition of compact swirling nozzle layout, compact nozzles with different flow rates are used to carry out outlet temperature distribution design. Through simulation of the inlet cross section, most of the cooling medium is distributed in the upper part of the circular outlet, and the concentration of cooling medium is lower in the lower part of the circular outlet. This is reflected in the outlet temperature distribution as the temperature is lower in the upper part of the circular outlet and higher in the lower part of the circular outlet. The higher temperature distribution is mainly concentrated in the area where the cooling medium is lacking.

[0065] like Figure 2 As shown, taking a certain section of the air intake as an example, with the central axis as the center, in order to truly reflect the temperature measurement results, pressure sensors are installed in a clockwise direction of 30° (this angle is for illustrative purposes only), with two evenly distributed around the circumference; traditional imported total temperature sensors are installed in a counterclockwise direction of 30°, with two evenly distributed around the circumference; waterproof imported total temperature sensors are installed in a counterclockwise direction of 45°, with two evenly distributed around the circumference; and traditional imported total temperature sensors are installed in a counterclockwise direction of 60°, with two evenly distributed around the circumference. In total, there are 6 imported total temperature sensors and 2 pressure sensors.

[0066] By evenly distributing traditional imported total temperature sensors on both sides of the waterproof imported total temperature sensor, the approximation to the same temperature measurement point can be maximized, resulting in a more accurate reflection of the temperature at the measurement location. Utilizing a dissimilar redundancy sensor allows for the acquisition of the engine inlet total temperature sensor time constant under actual installed conditions, resolving the discrepancy between time constants in wind tunnel testing and in-flight jet pre-cooling conditions. Furthermore, the dissimilar redundancy sensor enables compensation for rapidly changing signals over a large range, avoiding undercompensation and overcompensation issues caused by bandpass filtering from a single sensor.

[0067] The true engine inlet temperature cannot be obtained under the pre-cooling state of the jet, so a single sensor solution cannot accurately identify the time constant of the inlet total temperature sensor. This invention introduces a method of 6 non-similar redundancy temperature sensors and 2 pressure sensors, which can solve the problem of the inability to obtain the true time constant.

[0068] Since the airflow field inside the intake duct is constantly changing, circumferentially distributing the inlet total temperature sensor and pressure sensor can reflect the temperature and pressure at different locations inside the intake duct, thus obtaining more accurate measurement results.

[0069] This application employs anti-icing control accessories and anti-freezing solenoid valves for jet precooling water supply. The anti-icing control accessories use bleed air to externally purge the jet precooling control device and other accessories to prevent surface icing. After jet precooling stops working, the anti-freezing control accessories use bleed air to purge the water in the pipeline from the outlet of the three zones of the jet precooling control device to the jet precooling nozzle. Before entering the low-temperature environment, the water in the pipeline is purged in advance, thereby preventing the water in the pipeline from freezing. This not only reduces the risk of freezing during flight but also simplifies the storage and maintenance requirements for troops after landing. It expands the scope of domestic jet precooling applications that can be equipped with troops, allowing aircraft to continue to fly safely and with high maneuverability even in extremely cold and northern conditions.

[0070] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A jet precooling water supply antifreeze design architecture with uniform temperature measurement, characterized in that, include: Water source; Water pump; The water from the water source is pumped to the jet precooling control device; The jet precooling control device has a metering valve, and a sensing device connected to the jet precooling controller is installed on the metering valve. The sensing device senses the working parameters of the metering valve. The jet pre-cooling injection device sprays water from the jet pre-cooling control device onto the air intake duct; The jet precooling controller generates a control current for controlling the metering valve and a control current for controlling the water pump based on the sensing device of the metering valve and the sensing device installed at the engine inlet. The anti-icing module includes an anti-icing control accessory, which introduces engine bleed air into the jet pre-cooling injection device and blows anti-icing air onto the icing location of the jet pre-cooling injection device. The antifreeze module includes an antifreeze solenoid valve, which purges the easily frozen pipelines with gas from the aircraft gas cylinder. The sensor at the engine inlet is installed at the same axial position as the intake manifold. The sensing devices imported into the engine include: a set of waterproof imported total temperature sensors, two sets of traditional imported total temperature sensors, and a set of pressure sensors; Each set of waterproof inlet total temperature sensors includes two sensors, which are symmetrically distributed along the center of the inlet cross section. Each set of traditional imported total temperature sensors includes two sensors, and each set of traditional waterproof imported total temperature sensors is symmetrically distributed along the center of the inlet cross section. Each pressure sensor group consists of two sensors, and the pressure sensors in each group are symmetrically distributed along the center of the inlet cross section. Traditional imported total temperature sensors are located on both sides of waterproof imported total temperature sensors.

2. The jet precooling water supply antifreeze design architecture with uniform temperature measurement as described in claim 1, characterized in that, The angle between the axis of the traditional imported total temperature sensor passing through the center of the inlet section and the axis of the waterproof imported total temperature sensor passing through the center of the inlet section are the same for each group.

3. The jet precooling water supply antifreeze design architecture with uniform temperature measurement as described in claim 2, characterized in that, The angle between the axis of the waterproof imported total temperature sensor passing through the center of the imported section and the vertical axis of the imported section in the counterclockwise direction is 45 degrees; the included angle is 15 degrees.

4. The jet precooling water supply antifreeze design architecture with uniform temperature measurement as described in claim 1, characterized in that, The water pumps include: a normally open aircraft pump, a high-pressure water pump, and a water filter located between the aircraft pump and the high-pressure water pump. The high-pressure water pump returns the water from the aircraft pump to the water source when the jet precooling injection device stops working.

5. The jet precooling water supply antifreeze design architecture with uniform temperature measurement as described in claim 1, characterized in that, The metering valves include a first-zone metering valve, a third-zone metering valve, and a third-zone metering valve that operate in parallel. The first-zone metering valve, the first-zone metering valve, and the third-zone metering valve supply water to the jet precooling injection device individually or simultaneously.

6. The jet precooling water supply antifreeze design architecture for uniform temperature measurement as described in claim 1, characterized in that, The metering valve sensing device includes a displacement sensor that measures the opening degree of the metering valve and a pressure sensor that measures the outlet pressure of the metering valve.

7. The jet precooling water supply antifreeze design architecture for uniform temperature measurement as described in claim 1, characterized in that, The jet precooling controller is connected to a monitoring system, which displays the working status of the jet precooling controller.

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