Air intake distortion control simulation device for aero-engine aerodynamic stability evaluation test

Abstract

This application belongs to the field of aero-engine aerodynamic stability assessment technology, specifically relating to an aero-engine aerodynamic stability assessment test inlet distortion control simulation device, including: an annular cavity and an inlet pipe; the annular cavity is disposed between the air intake and the inlet of the aero-engine, and its inner wall has multiple jet holes distributed circumferentially; the inlet of the inlet pipe is connected to a high-pressure air source, and the outlet is connected to the outer wall of the annular cavity, connecting the annular cavity, and a flow regulating valve is provided on each inlet pipe.

Description

Technical Field

[0001] This application belongs to the field of aero-engine aerodynamic stability assessment technology, specifically relating to an aero-engine aerodynamic stability assessment test inlet distortion control simulation device. Background Technology

[0002] Currently, when assessing the aerodynamic stability of aero engines, perforated inserts are typically inserted into the air intake to create intake distortion. After the airflow enters the aero engine intake, it flows at high speed. When it encounters the obstruction of the insert, the flow pattern changes, forming a vortex region behind the insert, thus producing distortion. The intake pressure distortion created by this method is similar to the flow field at the aircraft intake exit during actual aero engine installation.

[0003] However, the insert plate has a single form and high processing cost. If it is processed into a hole-shaped insert plate for simulating distorted working conditions, it cannot be controlled in real time, especially the pulsation amount cannot be controlled, and it cannot simulate the periodic or non-periodic intake airflow field.

[0004] Furthermore, the insert is a solid-state hardware component that is inserted into the air intake of an aircraft engine. If it is damaged, it will endanger the safety of the aircraft engine. The insert also poses a risk of control abnormalities. If the insert cannot be removed in time, it may cause the aircraft engine to surge, endangering the use of the aircraft engine.

[0005] Because of the cavity effect of the insert plate, the accuracy of the aero-engine intake distortion is affected, impacting the distortion index and causing the distorted flow field to deviate from expectations. Since the insert plate is inserted from one side of the aero-engine intake duct, an "eccentric effect" exists, resulting in an incomplete distortion index that is difficult to efficiently and accurately simulate the actual operating conditions of an aero-engine. Furthermore, because the insert plate is fixed in position within the aero-engine intake duct, the distortion index cannot be dynamically adjusted, making real-time simulation of dynamic distortion impossible.

[0006] In view of the aforementioned technical deficiencies, this application is hereby filed. Summary of the Invention

[0007] The purpose of this application is to provide a simulation device for inlet distortion control in aero-engine aerodynamic stability evaluation tests, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A simulation device for inlet distortion control in an aerodynamic stability evaluation test of an aero-engine, characterized in that it includes: an annular cavity and an inlet pipe;

[0010] The annular cavity is located between the air intake and the inlet of the aero-engine, and its inner wall has multiple jet holes distributed circumferentially.

[0011] The inlet of the air intake pipe is connected to a high-pressure air source, and the outlet is connected to the outer wall of the annular cavity, connecting to the annular cavity. A flow regulating valve is installed on each air intake pipe.

[0012] According to at least one embodiment of this application, in the above-mentioned aero-engine aerodynamic stability evaluation test inlet distortion control simulation device, a plurality of radial baffles are provided in the annular cavity to divide its interior into a plurality of sector cavities.

[0013] There are multiple intake pipes, and the outlets connect to each sector of the air chamber.

[0014] According to at least one embodiment of this application, in the above-mentioned aero-engine aerodynamic stability evaluation test inlet distortion control simulation device, pressure gauges and flow meters are installed on each inlet pipe.

[0015] According to at least one embodiment of this application, in the above-mentioned aero-engine aerodynamic stability evaluation test inlet distortion control simulation device, each flow regulating valve, pressure gauge, and flow meter is connected to a controller. The controller collects pressure and flow through the pressure gauge and flow meter, and can control the opening of the flow regulating valve to regulate the pressure and flow.

[0016] According to at least one embodiment of this application, the above-mentioned aero-engine aerodynamic stability evaluation test inlet distortion control simulation device further includes a detector for collecting aero-engine inlet distortion parameters in conjunction with sensors. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the inlet distortion control simulation device for aero-engine aerodynamic stability evaluation test provided in this application embodiment;

[0018] Figure 2 This is a schematic diagram of the operation of the annular cavity provided in the embodiments of this application;

[0019] Figure 3 This is a partial structural diagram of the annular cavity provided in an embodiment of this application;

[0020] Figure 4 This is a square wave diagram of the airflow injected into the air intake of an aero-engine, provided in an embodiment of this application.

[0021] Figure 5 This is a sine wave diagram of the airflow injected into the air intake of an aero-engine, provided in an embodiment of this application.

[0022] in:

[0023] 1-Annular cavity; 2-Inlet pipe; 3-Inlet passage; 4-Inlet; 5-Flow regulating valve; 6-Pressure gauge; 7-Flow meter; 8-Controller; 9-Detector.

[0024] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0025] 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, and other related parts can be referred to the general design.

[0026] 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 word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0027] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable 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. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0028] A simulation device for inlet distortion control in aero-engine aerodynamic stability evaluation test, such as Figure 1 As shown, it includes an annular cavity 1 and an intake pipe 2.

[0029] The annular cavity 1 is located between the air intake 3 and the inlet 4 of the aero-engine, and its inner wall has multiple jet holes distributed circumferentially.

[0030] Multiple radial baffles are provided inside the annular cavity 1, dividing its interior into multiple sector cavities.

[0031] There are multiple intake pipes 2. The inlet is connected to a high-pressure air source, and the outlet is connected to the outer wall of the annular cavity 1, connecting to each sector cavity. Each intake pipe 2 is equipped with a flow regulating valve 5, a pressure gauge 6, and a flow meter 7.

[0032] The inlets of each air intake pipe 2 can be combined together to connect to a high-pressure air source.

[0033] Each flow regulating valve 5, pressure gauge 6, and flow meter 7 is connected to the controller 8. The controller 8 collects pressure and flow data through the pressure gauge 6 and flow meter 7, and can control the opening of the flow regulating valve 5 to regulate the pressure and flow.

[0034] The aero-engine aerodynamic stability evaluation test inlet distortion control simulation device disclosed in the above embodiments can introduce high-pressure gas into the annular cavity 1 through the inlet pipe 2, and then inject it into the aero-engine inlet through the jet orifice, such as... Figure 2 As shown, this creates disturbances in the airflow, resulting in distortion.

[0035] The jet flow rate variation control program can be preset through the controller 8 to programmatically control the flow rate and form of the airflow injected into the air intake of the aero-engine, thereby simulating the real operating conditions of the aero-engine and meeting the dynamic distortion requirements.

[0036] Two typical control methods for the airflow injected into the air intake of an aero-engine are square wave and sine wave, respectively. Figure 4-5 As shown, the frequency, upper and lower flow rates, and periodicity of the airflow injection are all adjustable. Furthermore, since the annular cavity 1 is divided into multiple sector cavities, the local structure is as follows... Figure 3 As shown, with different angular distributions, the flow rate of each sector cavity can be controlled to produce different waveforms, thereby simulating intake distortion under complex flow conditions.

[0037] Detector 9 can be set to work with corresponding sensors to collect air intake distortion parameters of aero-engines.

[0038] The aero-engine aerodynamic stability assessment test inlet distortion control simulation device disclosed in the above embodiments can actively control gaseous disturbance distortion. By changing the distortion form from a solid insert to a "gase insert", the distortion device can simulate the periodic and non-periodic inlet airflow field. It can realize the insertion of gaseous inserts at various circumferential angles, while ensuring the safety of aero-engine test. It can meet the requirements of stability, accuracy and speed, and is suitable for the distortion requirements of aero-engine aerodynamic stability assessment for various models.

[0039] The aero-engine aerodynamic stability assessment test inlet distortion control simulation device disclosed in the above embodiments has diverse gas injection methods, enabling control of pulsation amounts. It can simulate both periodic and non-periodic flow fields, is not limited by the type of insert plate, and has great operability. Moreover, since it is a gaseous insert plate, there is no risk of damage caused by solid ingestion into the aero-engine.

[0040] The above-described embodiment discloses an air intake distortion control simulation device for aero-engine aerodynamic stability evaluation test. The gaseous insert control system can be interlocked with the aero-engine surge system and also has a manual control function. If the aero-engine surges, the valve can be instantly closed to restore the aero-engine flow field to normal.

[0041] The aero-engine aerodynamic stability evaluation test inlet distortion control simulation device disclosed in the above embodiments can design the injection hole cross-section to be flush with the inlet plane, avoiding the cavity effect in the aero-engine inlet. Furthermore, it can inject gas from multiple angles to achieve distortion, and can also inject different waveforms or flow rates from multiple angles to achieve various combinations of distortions. Moreover, the gas flow rate can be adjusted in real time, providing extremely high safety.

[0042] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A simulation device for inlet distortion control in aero-engine aerodynamic stability evaluation test, characterized in that, include: Annular cavity (1), air inlet pipe (2); The annular cavity (1) is located between the air intake (3) and the inlet (4) of the aero-engine, and its inner wall has multiple jet holes distributed along the circumference; The inlet of the air inlet pipe (2) is connected to the high-pressure air source, and the outlet is connected to the outer wall of the annular cavity (1) and connected to the annular cavity (1). A flow regulating valve (5) is installed on each air inlet pipe (2).

2. The aeroengine aero-stability evaluation test inlet distortion control simulation apparatus of claim 1, wherein, Multiple radial baffles are provided inside the annular cavity (1) to divide its interior into multiple sector cavities; There are multiple intake pipes (2), and the outlets connect to each sector cavity.

3. The aeroengine aero-stability evaluation test inlet distortion control simulation apparatus of claim 2, wherein, Pressure gauges (6) and flow meters (7) are installed on each air inlet pipe (2).

4. The aeroengine aero-stability evaluation test inlet distortion control simulation apparatus of claim 3, wherein, Each flow regulating valve (5), pressure gauge (6), and flow meter (7) is connected to the controller (8). The controller (8) collects pressure and flow data through the pressure gauge (6) and flow meter (7), and can control the opening of the flow regulating valve (5) to regulate the pressure and flow.

5. The inlet distortion control simulation device for aero-engine aerodynamic stability evaluation test according to claim 4, characterized in that, It also includes a detector (9) used in conjunction with sensors to collect air intake distortion parameters of aero-engines.

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