Turbine power simulation device

Abstract

A turbine power simulation device for simulating the intake and exhaust of an aero-engine, wherein the turbine power simulation device comprises: a power source, which is arranged outside the engine part and generates power; a fan, which is arranged inside the engine part and generates thrust by rotating to do work on the ambient airflow; and a power transmission part, which transmits the power generated by the power source to the fan to drive the fan to rotate. Through the turbine power simulation device, not only can the larger power requirement be met, the test simulation is more in line with the similarity requirement, and the test result is more representative. Moreover, the occupied volume in the engine room is smaller, the energy consumption is smaller under the same output requirement, the required supporting facilities are simple, and the universality is good.

Description

TECHNICAL FIELD

[0001] The present application relates to a turbo power simulation device, and more particularly, to a turbo power simulation device capable of being used in a power influence simulation wind tunnel test. BACKGROUND

[0002] The intake and exhaust of an aircraft engine affect the aerodynamic characteristics of the aircraft. In the design and research of an aircraft, the influence of the intake and exhaust on the aerodynamic characteristics of the aircraft is generally obtained through a wind tunnel test. At present, a scheme of installing a power simulator in a model of an aircraft engine is generally adopted to simulate the power of the engine. However, because the space in the engine model is relatively small, on the basis of ensuring the effective flow channel of the duct, the space available for the built-in power simulation device is very small, and it is difficult to meet the power output requirement.

[0003] Specifically, the devices capable of being used in the power simulation of the wind tunnel test of an aircraft model mainly include two types: a high-pressure cold air ramjet turbine and an electric motor. The former generates driving force by introducing high-pressure cold air to impact a turbine, drives a front-end coaxial fan to rotate at a high speed, and realizes the simulation of the intake and exhaust. The latter drives the fan to rotate by using a high-power-density electric motor, thereby realizing the simulation of the intake and exhaust.

[0004] As a technology of using a high-pressure cold air ramjet turbine, for example, an engine simulation device is described in U.S. Patent Application No. US8082778B2. The engine simulation device uses high-pressure cold air to impact a turbine, thereby driving a fan at the front end to rotate at a high speed, and realizes the simulation of the intake and exhaust of the engine. However, because a large amount of high-pressure gas (usually about 70 atmospheres) needs to be consumed, the design of the supporting facilities is very complex, and the construction investment is very large. There are many technical difficulties in the use process, and a large and expensive auxiliary facility needs to be used, including a large-power air compressor, an air dryer, a high-pressure gas storage pipe, a high-pressure pipeline, a heating machine and other supporting facilities, which occupies a large area and lacks use convenience. In addition, the matching of the turbine and the fan is limited, and at most only 95% of the intake can be simulated, and the exhaust simulation of the inner duct cannot be controlled. There is a significant difference between the simulation and the real situation, and it is difficult to realize the simulation of the pressurization and the variable Reynolds number. In the specific test process, the tail vertebrae is easy to freeze, thereby affecting the test results.

[0005] As a technology using an electric motor, an electric motor simulation device is implemented in an electrically driven turbo power simulator of MTS Systems Corporation, which directly installs a high-performance electric motor in an engine model to drive a fan to rotate and introduce refrigerant to cool the electric motor. This scheme has strong practicability, but still has some problems. For example, since the electric motor is directly installed in the engine model, it occupies a large space in the engine, so that the cross section of the internal flow passage is small, the power consumption of the engine is greater than the actual demand, and the internal flow passage space is severely compressed and difficult to simulate the reverse thrust state. In addition, due to the space limitation in the engine model, the size of the electric motor that can be installed is limited, so that the power of the engine is limited, and the simulation of high Reynolds number state is limited. And since the refrigerant needs to be introduced to cool the electric motor in the engine model, the pipeline for the refrigerant flow needs to be arranged, which makes the design and processing of the model extremely complex.

[0006] Therefore, how to provide a new turbo power simulation device capable of meeting the large power demand and occupying a small volume in the engine room has become a technical problem to be solved. SUMMARY

[0007] The present disclosure is made to solve the above technical problems, and aims to provide a new turbo power simulation device capable of solving the technical problems in the prior art.

[0008] In order to achieve the purpose of the present disclosure, a turbo power simulation device is provided for simulating the intake and exhaust of an aero-engine, wherein the turbo power simulation device comprises: a power source, which is arranged outside the engine part and generates power; a fan, which is arranged inside the engine part and generates thrust by rotating and doing work on the surrounding airflow; and a power transmission part, which transmits the power generated by the power source to the fan to drive the fan to rotate.

[0009] According to the above configuration, since the power source is arranged outside the engine part, a larger space can be reserved in the engine part, so that the aerodynamic efficiency is higher, the required driving power is reduced, and a larger size power source can be used, which is helpful for high Reynolds number test and facilitates the engine to simulate various thrust conditions.

[0010] Preferably, the power source is arranged in the aircraft model.

[0011] According to the above-mentioned arrangement, by arranging the power source inside the model airplane, the design and installation of the supporting facilities can be made simpler, and the test can be carried out more easily. In addition, by transmitting the power through the power transmission part, the compatibility of the power source and the fan can be better, and the power test, such as the propeller power, can be applied to various types.

[0012] Preferably, the above-mentioned power source is an electric drive type.

[0013] According to the above-mentioned arrangement, by using the electric drive type power source, the efficiency of the power source can be improved, and the power calibration can be facilitated, thereby reducing the test difficulty and improving the test accuracy.

[0014] Preferably, a refrigerant is introduced into the above-mentioned power source to cool the above-mentioned power source.

[0015] According to the above-mentioned arrangement, the above-mentioned power source can be ensured to operate healthily.

[0016] Preferably, the power source output shaft of the above-mentioned power source and the fan shaft of the above-mentioned fan are not located on a straight line.

[0017] According to the above-mentioned arrangement, by transmitting the power generated by the power source to the fan through the power transmission part, the application range of the installation position of the power source can be wider.

[0018] Preferably, the above-mentioned power transmission part includes a transmission shaft and a gearbox, the above-mentioned transmission shaft receives the power generated by the above-mentioned power source and transmits it to the above-mentioned gearbox, and the above-mentioned gearbox adjusts the rotation speed and the torque.

[0019] According to the above-mentioned arrangement, by adjusting the rotation speed and the torque through the gearbox, the different requirements of the rotation speed and the torque of the upstream input and the downstream output can be matched.

[0020] Preferably, the above-mentioned transmission shaft is composed of a plurality of shafts connected together.

[0021] According to the above-mentioned arrangement, the installation and the threading of the transmission shaft are facilitated, thereby facilitating the test. BRIEF DESCRIPTION OF DRAWINGS

[0022] With reference to the above objects, the technical features of the present application are clearly described in the following technical solutions, and the advantages thereof are apparent from the following detailed description with reference to the accompanying drawings, which show preferred embodiments of the present application by way of example, but do not limit the scope of the inventive concept.

[0023] Figure 1 is a schematic diagram showing the arrangement state of the turbine power simulation device of the present application.

[0024] Figure 2is a schematic view showing the overall structure of the turbine power simulation device of the present application.

[0025] Explanation of symbols

[0026] 1 turbine power simulation device

[0027] 11 power source

[0028] 11a power source output shaft

[0029] 12 transmission shaft

[0030] 13 transmission

[0031] 13a transmission input shaft

[0032] 13b transmission output shaft

[0033] 14 fan

[0034] 14a fan shaft

[0035] B bearing

[0036] S mounting base

[0037] E engine section

[0038] M model airplane

[0039] G1, G2, G2', G3, G3', G4 gears DETAILED DESCRIPTION

[0040] Embodiments of the present application will now be described in detail with reference to examples shown in the drawings. Although the present application is described in conjunction with the exemplary embodiments, it will be understood that the description is not intended to limit the present application to the exemplary embodiments. On the contrary, the present application is intended to cover alternatives, modifications, equivalents and other embodiments which can be included within the spirit and scope of the present application as defined by the appended claims.

[0041] Hereinafter, with reference to Figure 1 , the arrangement state of the turbine power simulation device 1 of the present application will be described. Figure 1 is a schematic view showing the arrangement state of the turbine power simulation device 1 of the present application.

[0042] As Figure 1As shown, the power source 11 of the turbine power simulation device 1 of the present application is arranged on the mounting base S inside the aircraft model M and is connected with the fan 14 arranged in the engine section E through the power transmission mechanism, so as to transmit the power generated by the power source 11 to the fan 14, thereby performing the power simulation for the wind tunnel test.

[0043] Since the power source 11 is arranged outside the engine section E, a power source with larger size can be used, and the power of the power source can reach a larger value, thereby facilitating the high Reynolds number test and also facilitating the high Reynolds number test in a large span range.

[0044] In addition, since the power source 11 is arranged outside the engine section E, a larger space can be reserved in the engine section E, thereby facilitating the installation of the instruments and equipment required for the test, such as the rake body and other related devices for measuring the temperature and pressure of the region of interest.

[0045] Hereinafter, the overall structure of the turbine power simulation device 1 of the present application will be described with reference to the accompanying drawings. Figure 2 The overall structure of the turbine power simulation device 1 of the present application will be described. Figure 2 is a schematic view showing the overall structure of the turbine power simulation device 1 of the present application.

[0046] As shown in Figure 2 , the turbine power simulation device 1 of the present application mainly comprises a power source 11, a transmission shaft 12, a gearbox 13, a fan 14 and a plurality of bearings B.

[0047] The power source 11 is an electrically driven device that converts other energy (generally electric energy) into rotational mechanical energy. The power source 11 can be installed inside the aircraft model M or outside the wind tunnel model for testing. For example, when performing simulation tests of aircraft half-models or components, the power source 11 can be placed outside the test model. Here, only the case where the power source 11 is installed inside the aircraft model M is shown. The power source 11 is fixed on the mounting base S inside the aircraft model M by fasteners (not shown) or the like. If necessary, a temperature sensor, a vibration sensor, a rotational speed measuring device or the like can be arranged in the power source 11, and in addition, a refrigerant or the like can be introduced to cool the power source 11, thereby ensuring that the power source 11 operates healthily.

[0048] As described above, since the power source 11 is electrically driven, the design can be simplified and the efficiency can be improved, and it is also helpful for power calibration, thereby reducing the difficulty of the test and improving the accuracy of the test.

[0049] In addition, compared with the high-pressure cold air ramjet turbine of the prior art, the embodiment is not prone to icing during the test process. Moreover, the embodiment has good versatility and strong applicability to tail-suspended engines and half-models. In addition, the embodiment does not have turbine components, the internal resistance of the engine is small, and the airflow can pass through the inside more easily, thereby reducing the required input power.

[0050] The transmission shaft 12 is a component that transmits the rotational mechanical energy transmitted from the power source 11 to the required position. Gear wheels are provided at both ends of the transmission shaft 12, the gear wheel G2 at one end engages with the gear wheel G1 provided on the power source output shaft 11a of the power source 11, thereby receiving power from the power source 11, and the gear wheel G2' at the other end engages with the gear wheel G3 provided on the transmission shaft input shaft 13a of the transmission box 13, thereby transmitting the power transmitted from the power source 11 downward.

[0051] In addition, the transmission shaft 12 can be composed of a single shaft, but in order to meet specific space and other constraint requirements, the transmission shaft 12 can also be composed of multiple shafts connected together, which are supported by the main body components or bearings B to which they belong. As shown in the figure, an example of connecting three shafts together through two bearings B to form the transmission shaft 12 is shown, thereby facilitating the installation and arrangement of the transmission shaft 12. In addition, the specific number, position and form of the transmission shaft can be designed according to actual constraints and conditions.

[0052] The transmission box 13 is a device for adjusting the rotational speed and torque. In order to match the requirements of the rotational speed and torque of the upstream input and downstream output, the rotational speed and torque need to be adjusted by the transmission box 13, and the transmission system in the transmission box 13 can be designed according to the space of the fuselage and the mechanical characteristics. The transmission box input shaft 13a and the transmission box output shaft 13b are respectively provided at the input end and the output end of the transmission box 13, and gear wheels G3, G3' are respectively provided on the transmission box input shaft 13a and the transmission box output shaft 13b, the gear wheel G3 of the transmission box input shaft 13a engages with the gear wheel G2' of the transmission shaft 12, thereby receiving power from the transmission shaft 12, and the gear wheel G3' of the transmission box output shaft 13b engages with the gear wheel G4 provided on the fan shaft 14a of the fan 14, thereby transmitting power to the fan 14.

[0053] The fan 14 is fixed to the front end of the fan shaft 14a and rotates under the drive of the fan shaft 14a to do work on the surrounding airflow and thereby generate thrust, thereby realizing simulation of the engine thrust. The fan 14 can be similar to the fan of a turbine engine, or it can be similar to a propeller blade, and this component can also be used in model aircraft, thereby facilitating overall optimization design.

[0054] Further, as shown in the figure, the above-mentioned fan shaft 14a can be fixed at a desired position by a corresponding bearing B, generally coaxial with the simulated engine. Moreover, as shown in the figure, in the present embodiment, the power source output shaft 11a of the above-mentioned power source 11 and the fan shaft 14a of the above-mentioned fan 14 are not located on a straight line, but the power generated by the above-mentioned power source 11 is transmitted to the above-mentioned fan 14 through a power transmission part, so as to simulate the power of the engine.

[0055] Although the structure and working principle of the present application are described above in combination with the preferred embodiment, those skilled in the art should recognize that the above-mentioned examples are only for illustration and do not constitute a limitation on the present application. Modifications and variations of the present application can be made within the spirit and scope of the claims, and these modifications and variations will fall within the protection scope of the present application.

[0056] For example, in the present application, an example is shown in which the power source 11 is arranged inside the aircraft model M, but the present application is not limited thereto, and the above-mentioned power source 11 can also be installed outside the aircraft model, as long as it is not arranged inside the engine.

[0057] For example, in the present application, an example is shown in which the power source 11 is in an electric drive mode, but the present application is not limited thereto, and the above-mentioned power source 11 can also adopt other drive modes, as long as it can stably output power.

[0058] For example, in the present application, an example is shown in which the gearbox 13 is in the form of a box, but the present application is not limited thereto, and the specific form can be designed according to the available space, or a distributed multi-stage gearbox can be connected in series throughout the rotation transmission process to meet the needs, and in addition, the position of the gearbox can also be designed as needed.

Claims

1. A turbo power simulation device (1) for simulating the intake and exhaust of an aero engine, characterized in that, The turbine power simulation device (1) is characterized in that: a power source (11) is provided outside the engine section (E) and generates power; a fan (14) is provided inside the engine section (E) and generates thrust by rotating and working on ambient airflow; and a power transmission section transmits power generated by the power source (11) provided outside the engine section (E) to the fan (14) provided inside the engine section to drive the fan (14) to rotate, the power source output shaft (11a) of the power source (11) and the fan shaft (14a) of the fan (14) are not in a straight line, the power source (11) is provided inside the model airplane (M), the turbine power simulation device (1) is used for power impact simulation wind tunnel test.

2. The turbine power simulation device (1) according to claim 1, characterized in that: the power source (11) is electrically driven.

3. The turbine power simulation device (1) according to claim 1, characterized in that: a refrigerant is introduced into the power source (11) to cool the power source (11).

4. The turbine power simulation device (1) according to claim 1, characterized in that: the power transmission section includes a transmission shaft (12) and a gearbox (13), the transmission shaft (12) receives power generated by the power source (11) and transmits it to the gearbox (13), and the gearbox (13) adjusts the rotational speed and torque.

5. The turbine power simulation device (1) according to claim 4, characterized in that: the transmission shaft (12) is composed of a plurality of shafts connected together.

6. The turbine power simulation device (1) according to claim 4, characterized in that: both ends of the transmission shaft (12) are provided with gears, the gear (G2) at one end engages with the gear (G1) provided on the power source output shaft (11a) of the power source, and the gear (G2') at the other end engages with the gear (G3) provided on the gearbox input shaft (13a) of the gearbox (13).

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