Testing device for aero-engine starting system
By designing an aircraft engine starting system test device including an air source, an air turbine starter, a pressure sensor, a control device, a load simulation device, an adjustable opening starter air valve and a control valve, the difficulty in achieving the prior art is solved. The rich and effective testing of the starting system performance has been achieved, and the multi-condition test and performance analysis of the starting system has been achieved, ensuring accurate control of pressure input.
Patent Information
- Application Number
- CN202420389373.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-02-29
- Publication Date
- 2025-02-11
- Estimated Expiration
- 2034-02-28
AI Technical Summary
The existing aero engine starting system test devices are difficult to achieve rich and effective testing of the performance of the starting system, especially in multiple operating conditions, performance analysis and control are difficult.
An aircraft engine starting system test device is designed including an air source, an air turbine starter, a pressure sensor, a control device, a load simulation device, a starting air valve with adjustable opening and a control valve. The opening degree of the starter air valve is adjusted by controlling the control valve, and combined with real-time detection and control of the pressure sensor and control device, multiple operating conditions and performance analysis of the starter air valve are realized.
Effective simulation and testing of the aircraft engine starting system is realized, and the performance of the starting air valve can be analyzed and controlled in detail under multiple operating conditions to ensure the accurate control of the pressure input of the air turbine starter.
Smart Images
Figure CN222461037U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aviation engine test devices, in particular to an aviation engine starting system test device. Background Art
[0002] The starting system is an important part of the aircraft engine. The starting system turns the engine shaft to a certain speed to complete the starting. The engine is provided with compressed air by APU bleed air, ground air source or cross bleed air. The electronic controller sends a control command to the starting air valve to control the opening or closing of the starting air valve. When the starting air valve is in the open state, compressed air enters the air turbine starter. The air turbine starter converts the internal energy of the high-pressure gas into mechanical energy, and decelerates and increases torque. Finally, the output shaft outputs the shaft power to the accessory gearbox, and the accessory gearbox transmits the power to the engine. Summary of the invention
[0003] The utility model aims to provide an aircraft engine starting system test device which can carry out rich and effective testing on the performance of the aircraft engine starting system.
[0004] The utility model discloses an aircraft engine starting system test device, comprising an air source, an air turbine starter, a first pressure sensor, a second pressure sensor, a control device, a load simulation device, a starting air valve with adjustable opening, and a control valve for controlling the opening of the starting air valve, wherein the inlet of the starting air valve is connected to the air source through a first pipeline, the first pressure sensor is arranged on the first pipeline for detecting the pressure of the gas entering the inlet of the starting air valve, the outlet of the starting air valve is connected to the air turbine starter through a second pipeline, the second pressure sensor is arranged on the second pipeline for detecting the pressure of the gas output from the outlet of the starting air valve, the air turbine starter is drivingly connected to the load simulation device, the control device is signal-connected to the first pressure sensor, the second pressure sensor and the control valve, and the control device is configured to receive the detection results of the first pressure sensor and the second pressure sensor and control the control valve to adjust the opening of the starting air valve.
[0005] In some embodiments, the invention further includes a pressure regulating valve disposed on the first pipeline, wherein the pressure regulating valve is used to regulate the pressure of the gas entering the starting air valve.
[0006] In some embodiments, a third pipeline and a bypass valve arranged on the third pipeline are further included, the inlet and outlet of the third pipeline are respectively connected to the first pipeline and the outside, and the bypass valve is used to adjust the size of the flow area between the inlet and outlet of the third pipeline; and / or, a flow meter is also included on the first pipeline, and the flow meter is used to detect the flow of gas passing through the first pipeline.
[0007] In some embodiments, the control device includes a controller connected to the first pressure sensor, the second pressure sensor and the control valve signal, and a memory connected to the first pressure sensor and the second pressure sensor signal.
[0008] In some embodiments, the system further includes a temperature sensor disposed on the first pipeline for detecting the temperature of the gas entering the starting air valve, wherein the temperature sensor is connected to the memory signal.
[0009] In some embodiments, the method further includes a heater disposed on the first pipeline for heating the gas passing through the first pipeline.
[0010] In some embodiments, the load simulation device includes a transmission device drivingly connected to the air turbine starter, and the aircraft engine starting system test device also includes a speed sensor and a torque sensor arranged on the transmission device for respectively detecting the speed and torque output by the air turbine starter, and the control device is connected to the speed sensor and the torque sensor signals.
[0011] In some embodiments, the load simulation device further comprises an inertia simulation component drivingly connected to the transmission device, and the transmission ratio of the transmission device is variable.
[0012] In some embodiments, it also includes an on-off valve disposed on the first pipeline and connected to the control device signal.
[0013] Based on the aircraft engine starting system test device provided by the utility model, by setting components such as a starting air valve with adjustable opening, a first pressure sensor, a second pressure sensor, a control valve, and a control device, it is possible to effectively simulate and test the aircraft engine starting system. The control valve can adjust the opening of the starting air valve to multiple degrees to achieve multi-condition testing of the starting air valve. At the same time, it is also possible to record the inlet and outlet pressures of the starting air valve during the test and perform a detailed analysis of the performance of the starting air valve. It is also possible to perform closed-loop control of the output gas pressure of the starting air valve to achieve accurate control of the pressure input of the air turbine starter.
[0014] Other features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings:
[0016] Figure 1 The present invention is a schematic diagram of the structure and principle of an aircraft engine starting system test device according to an embodiment of the present invention. DETAILED DESCRIPTION
[0017] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means a limitation on the utility model and its application or use. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model.
[0018] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values of the parts and steps set forth in these embodiments do not limit the scope of the utility model. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.
[0019] In the description of the present invention, it should be understood that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.
[0020] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0021] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.
[0022] The aircraft engine starting system test device of this embodiment includes an air source 4, an air turbine starter 2, a first pressure sensor, a second pressure sensor, a control device 8, a load simulation device 3, a starting air valve 1 with adjustable opening, and a control valve for controlling the opening of the starting air valve 1.
[0023] The air source 4 can be APU bleed air, ground air source or cross bleed air. The inlet of the starting air valve 1 is connected to the air source 4 through the first pipeline 51. The adjustable opening of the starting air valve 1 means that the starting air valve has at least three openings. In the embodiment shown in the figure, the starting air valve is a butterfly valve with a continuously adjustable opening, that is, the opening of the starting air valve can be adjusted steplessly. The control valve is used to adjust the opening of the starting air valve. In the embodiment shown in the figure, the control valve is a solenoid valve connected to the control device signal.
[0024] The first pressure sensor 51 is arranged on the first pipeline 61 to detect the pressure of the gas entering the inlet of the starting air valve 1. The outlet of the starting air valve 1 is connected to the air turbine starter 2 through the second pipeline 62. The second pressure sensor 52 is arranged on the second pipeline 62 to detect the pressure of the gas output from the outlet of the starting air valve 1. The first pressure sensor and the second pressure sensor can be pressure gauges.
[0025] The air turbine starter 2 is drivingly connected to the load simulation device 3, that is, the air turbine starter 2 can drive the load simulation device 3 to operate. In the embodiment shown in the figure, the load simulation device includes a flywheel for simulating a turbine.
[0026] The control device 8 is connected to the first pressure sensor 51, the second pressure sensor 52 and the control valve signal, and the control device 8 is configured to receive the detection results of the first pressure sensor 51 and the second pressure sensor 52 and control the control valve to adjust the opening of the starting air valve 1. In the embodiment shown in the figure, except for the arrow of the flow meter 72, the remaining solid arrows represent the transmission of data signals, and the dotted arrows represent the flow of gas.
[0027] After the compressed gas in the gas source enters the starting air valve through the first pipeline, it enters the air turbine starter 2 through the starting air valve. The air turbine starter converts the internal energy of the high-pressure gas into mechanical energy, and then drives the load simulation device to operate to simulate the driving turbine. The aircraft engine starting system test device of this embodiment can effectively simulate and test the aircraft engine starting system by setting components such as the starting air valve 1 with adjustable opening, the first pressure sensor 51, the second pressure sensor 52, the control valve and the control device 8. The control valve can adjust the opening of the starting air valve 1 to realize the multi-operating condition test of the starting air valve 1. At the same time, it can also realize the recording of the inlet and outlet pressures of the starting air valve 1 during the test, and the performance of the starting air valve 1 can be analyzed in detail. The control device can also control the control valve according to the detection result of the second pressure sensor to adjust the opening of the starting air valve, so that the closed-loop control of the output gas pressure of the starting air valve 1 can be realized, and the accurate control of the pressure input of the air turbine starter 2 can be realized.
[0028] In some embodiments, the aircraft engine starting system test device further includes a pressure regulating valve 73 disposed on the first pipeline 61 , and the pressure regulating valve 73 is used to adjust the pressure of the gas entering the starting air valve 1 .
[0029] In some embodiments, the aircraft engine starting system test device further includes a third pipeline 63 and a bypass valve 75 disposed on the third pipeline 63. The inlet and outlet of the third pipeline 63 are respectively connected to the first pipeline 61 and the outside. The bypass valve 75 is used to adjust the size of the flow area between the inlet and outlet of the third pipeline 63. By setting the third pipeline and the bypass valve, the flow rate of the gas output from the third pipeline is adjusted by adjusting the opening of the bypass valve, so that the flow rate of the gas entering the starting air valve can be adjusted. In some embodiments, the aircraft engine starting system test device further includes a flow meter 72 disposed on the first pipeline 61. The flow meter 72 is used to detect the flow rate of the gas passing through the first pipeline 61.
[0030] In some embodiments, the control device 8 includes a controller connected to the first pressure sensor, the second pressure sensor and the control valve signal, and a memory connected to the first pressure sensor and the second pressure sensor signal.
[0031] In some embodiments, the aircraft engine starting system test device further includes a temperature sensor 76 disposed on the first pipe 61 for detecting the temperature of the gas entering the starting air valve 1, and the temperature sensor 76 is connected to the memory signal. The memory can be provided to record the detection results of the first pressure sensor, the second pressure sensor, the temperature sensor and other detection elements.
[0032] In some embodiments, the aircraft engine starting system test device further includes a heater 71 disposed on the first pipe 61 for heating the gas passing through the first pipe 61. The test device can simulate the operating conditions of a real engine starting system and provide the starting system with continuously adjustable air supply pressure, air supply temperature and air supply flow.
[0033] In some embodiments, the load simulation device 3 includes a transmission device connected to the air turbine starter 2, and the aircraft engine starting system test device also includes a speed sensor and a torque sensor provided on the transmission device for detecting the speed and torque output by the air turbine starter 2, respectively. The control device 8 is connected to the speed sensor and the torque sensor signals. In some embodiments, the load simulation device 3 also includes an inertia simulation component connected to the transmission device, and the transmission ratio of the transmission device is variable. In this embodiment, the load simulation device includes a transmission device and a flywheel. By changing the transmission ratio of the transmission device, the rotational inertia of the load simulation device driven by the air turbine starter can be changed to achieve simulation of various engine loads.
[0034] In some embodiments, the aircraft engine starting system test device further includes an on-off valve 74 provided on the first pipeline 61 and connected to the control device 8 by signal. The control device can monitor the speed signal of the air turbine starter. When the air turbine starter reaches the disengagement speed, the controller controls the starting air valve to close, and cuts off the air source of the air turbine starter through the on-off valve 74.
[0035] In some embodiments, the aircraft engine starting system test device further includes a host computer 9, such as a computer, which is connected to the control device by signal, to achieve convenient control of the control device.
[0036] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model has been described in detail with reference to the preferred embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the utility model can still be modified or some technical features can be replaced by equivalents without departing from the spirit of the technical solution of the utility model, which should be included in the scope of the technical solution for protection of the utility model.
Claims
1. An aircraft engine starting system test device, characterized in that: The invention comprises an air source, an air turbine starter, a first pressure sensor, a second pressure sensor, a control device, a load simulation device, a starting air valve with an adjustable opening, and a control valve for controlling the opening of the starting air valve, wherein the inlet of the starting air valve is connected to the air source through a first pipeline, the first pressure sensor is arranged on the first pipeline for detecting the pressure of the gas entering the inlet of the starting air valve, the outlet of the starting air valve is connected to the air turbine starter through a second pipeline, the second pressure sensor is arranged on the second pipeline for detecting the pressure of the gas output from the outlet of the starting air valve, the air turbine starter and the load simulation device are drivingly connected, the control device is signal-connected to the first pressure sensor, the second pressure sensor and the control valve, and the control device is configured to receive the detection results of the first pressure sensor and the second pressure sensor and control the control valve to adjust the opening of the starting air valve.
2. The aircraft engine starting system test device according to claim 1, characterized in that: It also includes a pressure regulating valve arranged on the first pipeline, and the pressure regulating valve is used to adjust the pressure of the gas entering the starting air valve.
3. The aircraft engine starting system test device according to claim 1, characterized in that: It also includes a third pipeline and a bypass valve arranged on the third pipeline, the inlet and outlet of the third pipeline are respectively connected to the first pipeline and the outside, and the bypass valve is used to adjust the size of the flow area between the inlet and outlet of the third pipeline; and / or, it also includes a flow meter arranged on the first pipeline, and the flow meter is used to detect the flow of gas passing through the first pipeline.
4. The aircraft engine starting system test device according to claim 1, characterized in that: The control device includes a controller connected to the first pressure sensor, the second pressure sensor and the control valve signal, and a memory connected to the first pressure sensor and the second pressure sensor signal.
5. The aircraft engine starting system test device according to claim 4, characterized in that: It also includes a temperature sensor disposed on the first pipeline for detecting the temperature of the gas entering the starting air valve, and the temperature sensor is connected to the memory signal.
6. The aircraft engine starting system test device according to claim 4 or 5, characterized in that: The system also includes a heater disposed on the first pipeline for heating the gas passing through the first pipeline.
7. The aircraft engine starting system test device according to claim 1, characterized in that: The load simulation device includes a transmission device drivingly connected to the air turbine starter, and the aircraft engine starting system test device also includes a speed sensor and a torque sensor arranged on the transmission device for respectively detecting the speed and torque output by the air turbine starter, and the control device is connected to the speed sensor and the torque sensor signals.
8. The aircraft engine starting system test device according to claim 7, characterized in that: The load simulation device further comprises an inertia simulation component drivingly connected to the transmission device, and the transmission ratio of the transmission device is variable.
9. The aircraft engine starting system test device according to claim 1, characterized in that: It also includes an on-off valve disposed on the first pipeline and connected to the control device signal.