A ground high and low temperature starting test equipment for aircraft engines

Abstract

The present application belongs to the field of aircraft engine testing, and particularly relates to a ground high and low temperature starting test equipment for an aircraft engine, an air source station, a drying system connected to the air source, an air filter connected to the drying system; a refrigeration system connected to the air filter, a blender connected to the refrigeration system, a test chamber connected to the blender, and an exhaust device connected to the test chamber; a first pipeline is connected in parallel at both ends of the drying system, and a second pipeline is connected in parallel at both ends of the refrigeration system, and a heat exchange device for heating the pipeline gas is provided at the first pipeline or the second pipeline; the drying system includes multiple parallel drying towers, and the refrigeration system includes multiple turbine-compressor units consisting of refrigeration turbines and load compressors; the present application has the test capability of high temperature and low temperature starting at the same time by switching the air supply path, and can obtain the starting characteristics of the engine at different temperatures within a shorter period.

Description

Technical Field

[0001] The present application relates to the field of aviation engine testing, and in particular to a ground high and low temperature starting test device for an aviation engine. Background Art

[0002] my country has a vast territory, with large temperature differences between the north and the south. To meet the needs of aircraft, aircraft engines need to have good starting capabilities in high and low temperature environments. The simplest and most direct way to conduct high and low temperature starting tests is to conduct starting tests on a ground test bench in a specific area and during a specific time period. Domestically, tests have been conducted on low-temperature engine starting using a high-altitude platform equipped with an insulation box. The high-altitude platform air supply equipment is used to supply air to the flow path inside the engine. After a period of low-temperature insulation, the windmill is stopped and the engine is started at low temperature. The No. 6 open-air test bench in the test area of ​​RR Company in the UK uses a movable box to insulate the engine with liquid nitrogen. After the insulation is completed, the box is removed for low-temperature engine starting. Currently, most high-temperature starting tests are verified in tropical field environments, and there is no equipment specifically for high-temperature testing.

[0003] The above methods all have defects to varying degrees, such as:

[0004] 1. Starting tests in specific areas and time periods are consistent with the actual operating conditions of the engine, but this method is expensive and time-consuming;

[0005] 2. The low-temperature insulation method of the high-altitude typhoon vehicle is that the engine rotor keeps running due to the ram pressure, and the temperature of the bearing and lubricating oil system cannot be reduced to the specified temperature, which does not meet the true initial low-temperature state of the engine;

[0006] 3. During the open-air starting test with a movable insulation box, when the box is removed, the air inhaled by the engine is uncooled air, which cannot fully simulate the low-temperature starting process environment and cannot fully meet the requirements of high and low temperature starting tests.

[0007] Therefore, the design fully meets the requirements for high and low temperature starting tests. It is a technical problem that needs to be solved to have an aircraft engine high and low temperature starting test equipment with a wide temperature adjustment and long endurance insulation capability. Summary of the Invention

[0008] In order to solve the above problems, the present application provides an aircraft engine ground high and low temperature starting test equipment, comprising:

[0009] An air source station, a drying system connected to the air source, an air filter connected to the drying system; a refrigeration system connected to the air filter, a blender connected to the refrigeration system, a test chamber connected to the blender, and an exhaust device connected to the test chamber; a first pipeline connected in parallel at both ends of the drying system, a second pipeline connected in parallel at both ends of the refrigeration system, and a heat exchange device for heating the pipeline gas provided at the first pipeline or the second pipeline; the drying system includes multiple parallel drying towers, and the refrigeration system includes multiple turbine-compressor units consisting of refrigeration turbines and load compressors;

[0010] The air source station, the drying system, the air filter, the refrigeration system, and the blender form a low-temperature system for providing cold air to the test chamber;

[0011] The gas source station, the first pipeline, the second pipeline, the blender, the air filter, the test chamber, and the exhaust device form a high-temperature system for providing hot air to the test chamber;

[0012] Diversion branches are respectively provided on both ends of the drying machine, the refrigeration system and the blender to be connected with the exhaust device.

[0013] Preferably, the exhaust device includes a main exhaust, an induced exhaust and a starter exhaust; wherein the maximum flow of the main exhaust is greater than the maximum flow of the induced exhaust and the maximum flow of the starter exhaust; the induced exhaust is induced by compressed gas; wherein, when the test chamber is insulated, the induced exhaust is closed and the main exhaust opening is reduced; when the test chamber is temperature-adjusted, the main exhaust is opened and the induced exhaust is opened; during the engine starting process of the test chamber, the main exhaust and the induced exhaust are opened to the maximum.

[0014] Preferably, the test chamber is connected to an air intake tower, which is connected to the atmosphere and is used to provide room temperature air to the test chamber.

[0015] Preferably, the outlet end of the drying tower is connected to an electric air heater and a blower respectively; the electric air heater heats the air blown in by the blower, and the heated air enters the drying tower to dry the moisture-saturated desiccant in the drying tower.

[0016] Preferably, a third pipeline is connected in parallel at both ends of the electric air heater, and a fourth pipeline is connected in parallel at the inlet of the blower and the inlet of the drying tower; the blower blows normal temperature air into the drying tower through the third pipeline and returns to the inlet of the blower from the fourth pipeline.

[0017] Preferably, regulating valves are provided at the inlet and outlet of the refrigeration turbine and the load compressor for adjusting the refrigeration flow and the turbine speed.

[0018] Preferably, a dew point meter is provided at the inlet of the refrigeration turbine.

[0019] Preferably, a high-position fuel tank is provided in the test chamber, and the position of the high-position fuel tank is higher than the engine to be tested.

[0020] When cooling through the aircraft engine ground high and low temperature starting test equipment, the number of the drying towers and the number of turbine-compressor units can be matched according to demand.

[0021] Advantages of this application include:

[0022] 1. By switching the air supply path, the system has the ability to test both high-temperature and low-temperature starting, and can obtain the starting characteristics of the engine at different temperatures in a relatively short period of time;

[0023] 2. Through the reuse of the drying system and the flexible adjustment of the refrigeration flow, the test energy consumption and test costs can be greatly reduced;

[0024] 3. The cabin pressure is balanced through the integral air supply from the top, which provides heat preservation capability when the engine is completely stationary.

[0025] 4. By adjusting the intake and exhaust air in the test chamber and pre-loading fuel in the high-position fuel tank, the consistency of the intake air temperature, fuel temperature and target simulation temperature during the starting process is ensured, obtaining more realistic engine starting parameters.

[0026] 5. The drying system of the present application has a desiccant recycling and regeneration function, which enables the drying system to be reused. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of a high and low temperature starting test device according to a preferred embodiment of the present application;

[0028] Figure 2 This is a partial enlarged view of a drying system in a preferred embodiment of the present application;

[0029] Figure 3 This is the operating characteristics of the refrigeration turbine in a preferred embodiment of the present application;

[0030] Figure 4 This is the working characteristic of the load compressor in a preferred embodiment of the present application;

[0031] Figure 5 This is a partial enlarged view of the high-position oil tank in the test cabin of a preferred embodiment of the present application. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and should not be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in conjunction with the drawings.

[0033] The present application provides an aircraft engine ground high and low temperature starting test equipment, comprising:

[0034] An air source station, a drying system connected to the air source, an air filter connected to the drying system; a refrigeration system connected to the air filter, a blender connected to the refrigeration system, a test chamber connected to the blender, and an exhaust device connected to the test chamber; a first pipeline connected in parallel at both ends of the drying system, a second pipeline connected in parallel at both ends of the refrigeration system, and a heat exchange device for heating the pipeline gas provided at the first pipeline or the second pipeline; the drying system includes multiple parallel drying towers, and the refrigeration system includes multiple turbine-compressor units consisting of refrigeration turbines and load compressors;

[0035] The air source station, the drying system, the air filter, the refrigeration system, and the blender form a low-temperature system for providing cold air to the test chamber;

[0036] Combined with attachment Figure 1 : Low temperature system: The low temperature starting air supply enters the test chamber through valve G17, valve G15, drying system, valve G9, valve G13, air filter, valve Z1, valve Z3, turbine refrigeration system, valve Z11, mixer, and valve Z13; valves G14, G18, Z10, and Z14 are set on the air supply path to divert the air, which can adjust the air intake flow and can also be used for emergency emptying.

[0037] The gas source station, the first pipeline, the air filter, the second pipeline, and the blender form a high-temperature system for providing hot gas to the test chamber;

[0038] High temperature system: The high temperature starting air supply enters the test chamber through valve G17, valve G16, valve G13, air filter, valve Z1, valve Z2, mixer, and valve Z13; valves G14, G18, Z10, and Z14 are set on the air supply path to divert the air, which can adjust the air intake flow and can also be used for emergency emptying.

[0039] Diversion branches are respectively provided on both ends of the drying machine, the refrigeration system and the blender to be connected with the exhaust device.

[0040] Its working principle is to combine the Figure 1 The system intake is on the left, and the exhaust is on the right. After the main intake, the air can be dehumidified through a parallel dryer or directly supplied to a blender for temperature regulation. The dehumidified air then passes through a parallel turbine-compressor unit for cooling. After cooling, it is blended with the main intake air. After adjusting the ratio to the target temperature, it is supplied to the test chamber for testing. Each sub-link is equipped with a pressure relief and venting system to ensure system safety.

[0041] Preferably, the exhaust device includes a main exhaust, an induced exhaust and a starter exhaust; wherein the maximum flow of the main exhaust is greater than the maximum flow of the induced exhaust and the maximum flow of the starter exhaust; the induced exhaust is induced by compressed gas; wherein, when the test chamber is insulated, the induced exhaust is closed and the main exhaust opening is reduced; when the test chamber is temperature-adjusted, the main exhaust is opened and the induced exhaust is opened; during the engine starting process of the test chamber, the main exhaust and the induced exhaust are opened to the maximum.

[0042] The above preferred features are combined with the attached Figure 1 Note: The air intake in the test chamber is top intake to achieve pressure balance in the chamber. There is no pressure difference between the engine inlet and outlet, so it can ensure that the engine rotor is in a natural static state during the pipe intake process. The exhaust in the chamber is divided into three parts: main exhaust, induced exhaust and starter exhaust, which can be independently controlled by valves 5, 6 and 7. During the insulation process, the induced exhaust is closed and the main exhaust opening is reduced to effectively reduce gas source consumption. During the temperature adjustment process, the main exhaust is opened and the induced exhaust is opened moderately to increase the fluidity in the test chamber and improve the temperature adjustment rate. During the engine starting process, the main exhaust and induced exhaust are opened to the maximum to avoid the influence of heat backflow of engine exhaust. The starter exhaust is an independent channel, mainly to avoid the influence of starter exhaust on the temperature of the test chamber.

[0043] Preferably, the test chamber is connected to an air intake tower, which is connected to the atmosphere and is used to provide room temperature air to the test chamber.

[0044] Preferably, the outlet end of the drying tower is connected to an electric air heater and a blower respectively; the electric air heater heats the atmosphere blown in by the blower, and the heated atmosphere enters the drying tower to dry the moisture-saturated desiccant in the drying tower. A third pipeline is connected in parallel at both ends of the electric air heater, and a fourth pipeline is connected in parallel at the inlet of the blower and the inlet of the drying tower; the blower blows normal temperature air into the drying tower through the third pipeline and returns to the inlet of the blower from the fourth pipeline.

[0045] The above preferred features are combined with the attached Figure 1 Note: The drying system includes drying working mode, self-circulation working mode and regeneration working mode;

[0046] 1) Drying working mode: Mainly used in low temperature starting test, wet air enters the dryer through G15 and is transported to the refrigeration system through G9;

[0047] 2) Self-circulation mode: It is mainly used to quickly cool down the desiccant after high-temperature drying to achieve the purpose of lowering the initial temperature of the air entering the refrigeration system, which can greatly reduce the load of the refrigeration system. The working path is: blower, G10, dryer, G11, and return to the blower cycle;

[0048] 3) Regeneration mode: When the dryer is saturated with moisture, regeneration is required. The atmosphere is transported from the blower to the electric heater through the valve of drum 3 for heating. The desiccant is dried through the valve of drum 1 in the opposite direction of the drying working path and finally emptied through G14. The reverse drying path can make the desiccant regeneration effect better.

[0049] Preferably, regulating valves are provided at the inlets and outlets of the refrigeration turbine and the load compressor for adjusting the refrigeration flow and turbine speed, and a dew point meter is provided at the inlet of the refrigeration turbine.

[0050] Combined with attachment Figure 1 With attached Figure 2 A specific implementation method for a refrigeration system is provided. The refrigeration system consists of three parallel turbine-compressor units. The load compressor consumes the residual work of the refrigeration turbine to achieve self-balancing. The maximum air flow rate produced by a single turbine is 13.5 kg / s, and the maximum temperature drop is 105°C. The number of dryers and turbine units to be used is selected based on the refrigeration flow rate:

[0051] 1) When the cooling capacity is below 10kg / s, a single turbine unit with two dryers is used;

[0052] 2) The cooling capacity is between 10kg / s and 20kg / s, using two turbines with three dryers;

[0053] 3) If the cooling capacity is above 20kg / s, three turbines are used with four dryers.

[0054] In order to prevent the low-temperature air after turbine refrigeration from freezing due to high humidity, a dew point meter is installed at the turbine inlet. During the test, the temperature of the turbine after refrigeration should not be lower than the dew point temperature by more than 10℃. Regulating valves are installed at the inlet and outlet of the refrigeration turbine and the load compressor to adjust the parameters such as the refrigeration flow rate and turbine speed. The working characteristics of the refrigeration turbine and the load compressor during the refrigeration process are shown in Figure 2. Figure 3 、 Figure 4 As shown;

[0055] Combine Figure 1 In order to prevent residual water vapor and foreign matter in the pipeline from affecting the engine, a two-stage purge path is set in the system, divided according to the front and back of the air filter:

[0056] 1) Prioritize purging before air filtration: the main intake air is purged and exhausted through valves G17, G16, G13, and G18;

[0057] 2) Then, perform post-filter purge: the main intake air is purged and exhausted through valves G17, G16, G13, Z1, Z2, and Z14;

[0058] like Figure 5 As shown, in order to ensure that the temperature of the engine starting oil is consistent with the ambient temperature in the cabin, a high-position fuel tank is set in the test cabin. See the schematic diagram Figure 5 During the insulation process, the temperature gradually converges to the cabin temperature through heat exchange. The high-level fuel tank is connected to the external oil depot and can be controlled by valve 8 for oil replenishment. The fuel tank is set to release air at a high point and oil at a low point. Before the test, it must be pre-filled with sufficient fuel. The potential energy is used to independently supply oil to the engine and starter.

[0059] This application 1. By switching the air supply path, it has the ability to test high-temperature and low-temperature starts at the same time, and can obtain the starting characteristics of the engine at different temperatures in a shorter period; 2. By reusing the drying system and flexibly adjusting the refrigeration flow, it can greatly reduce the test energy consumption and reduce the test cost; 3. Through the overall air supply at the top, the pressure balance in the cabin is maintained, and the heat preservation ability is possessed when the engine is fully stationary; 4. Through the intake and exhaust adjustment of the test cabin and the pre-loading of fuel in the high-position fuel tank, the consistency of the intake air temperature and fuel temperature during the starting process with the target simulation temperature is ensured, and more realistic engine starting parameters are obtained.

[0060] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An aircraft engine ground high and low temperature starting test equipment, characterized in that: include: An air source station, a drying system connected to the air source, and an air filter connected to the drying system; A refrigeration system connected to the air filter, a blender connected to the refrigeration system, a test chamber connected to the blender, and an exhaust device connected to the test chamber; a first pipeline is connected in parallel at both ends of the drying system, a second pipeline is connected in parallel at both ends of the refrigeration system, and a heat exchange device for heating the pipeline gas is provided at the first pipeline or the second pipeline; the drying system includes multiple parallel drying towers, and the refrigeration system includes multiple turbine-compressor units consisting of refrigeration turbines and load compressors; The air source station, the drying system, the air filter, the refrigeration system, and the blender form a low-temperature system for providing cold air to the test chamber; The gas source station, the first pipeline, the air filter, the second pipeline, and the blender form a high-temperature system for providing hot gas to the test chamber; Diversion branches are respectively provided on both ends of the drying machine, the refrigeration system and the blender to be connected with the exhaust device.

2. The aircraft engine ground high and low temperature starting test equipment according to claim 1, characterized in that: The exhaust device includes a main exhaust, an induced exhaust and a starter exhaust; wherein the maximum flow of the main exhaust is greater than the maximum flow of the induced exhaust and the maximum flow of the starter exhaust; the induced exhaust is induced by compressed gas; wherein, when the test chamber is insulated, the induced exhaust is closed and the main exhaust opening is reduced; when the test chamber is temperature-adjusted, the main exhaust is opened and the induced exhaust is turned on; during the engine starting process in the test chamber, the main exhaust and the induced exhaust are opened to the maximum.

3. The aircraft engine ground high and low temperature starting test equipment according to claim 1, characterized in that: The test chamber is connected to an air intake tower, which is in communication with the atmosphere and is used to provide room temperature air to the test chamber.

4. The aircraft engine ground high and low temperature starting test equipment according to claim 1, characterized in that: The outlet end of the drying tower is connected to an electric air heater and a blower respectively; the electric air heater heats the air blown in by the blower, and the heated air enters the drying tower to dry the moisture-saturated desiccant in the drying tower.

5. The aircraft engine ground high and low temperature starting test equipment according to claim 4, characterized in that: A third pipeline is connected in parallel at both ends of the electric air heater, and a fourth pipeline is connected in parallel at the inlet of the blower and the inlet of the drying tower; the blower blows room temperature air into the drying tower through the third pipeline and returns to the inlet of the blower from the fourth pipeline.

6. The aircraft engine ground high and low temperature starting test equipment according to claim 1, characterized in that: The inlet and outlet of the refrigeration turbine and the load compressor are both provided with regulating valves for adjusting the refrigeration flow and the turbine speed.

7. The aircraft engine ground high and low temperature starting test equipment according to claim 6, characterized in that: A dew point meter is provided at the inlet of the refrigeration turbine.

8. The aircraft engine ground high and low temperature starting test equipment according to claim 1, characterized in that: A high-position oil tank is provided in the test chamber, and the position of the high-position oil tank is higher than the engine to be tested.

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