A turbine engine inlet flow field scanning test apparatus

Abstract

This invention provides a turbine engine intake airflow field scanning test device, including a casing, a mounting bracket, and a fan shaft. The fan shaft is rotatably connected to the bracket. A fan blade is circumferentially fixed to the fan shaft, passing through a mesh cover, and a scanning rod is mounted thereon. Several pressure sensors are mounted on the scanning rod. A mesh cover is installed at the air inlet of the casing, and pressure probes are fixed to the surface of the mesh cover. When the fan shaft rotates, it drives the scanning rod to rotate. The pressure sensors and pressure probes work together to detect the total intake pressure distortion across the entire frequency range. The pressure sensors and pressure probes are respectively connected to a controller. In this turbine engine intake airflow field scanning test device, pressure probes are fixed to the surface of the mesh cover at the air inlet of the engine casing, and several pressure sensors are also mounted on the scanning rod. Through the arrangement of the pressure sensors and pressure probes, the total intake pressure distortion across the entire frequency range can be monitored in real time as the scanning rod rotates.

Description

Technical Field

[0001] This invention belongs to the field of turbofan engine technology, and in particular relates to a turbofan engine intake airflow field scanning test device. Background Technology

[0002] The study of the inlet flow field of turbine engines has become an important aspect of modern engine development. Understanding the degree of flow field distortion, especially the distortion of total intake pressure, is a crucial means of improving turbine engine performance. Currently, conventional technologies mostly employ simulation calculations. Even when conducting real tests in the turbine engine inlet, they often use fixed sensors. However, this still cannot provide a full-frequency domain understanding of the total intake pressure distortion. Summary of the Invention

[0003] In view of this, the present invention aims to provide a turbine engine intake airflow field scanning test device to solve the problem of not being able to grasp the intake total pressure distortion in the full frequency domain.

[0004] To achieve the above objectives, the technical solution of the present invention is implemented as follows:

[0005] A turbine engine intake airflow field scanning test device includes a housing, a mounting bracket, and a fan shaft. The fan shaft is rotatably connected to the mounting bracket. A scanning rod is mounted circumferentially on the fan shaft, passing through a mesh cover. Several pressure sensors are mounted on the scanning rod. A mesh cover is installed at the air inlet of the housing, and pressure probes are fixed on the surface of the mesh cover. When the fan shaft rotates, it drives the scanning rod to rotate. The pressure sensors and pressure probes cooperate to detect the total intake pressure distortion in the full frequency domain. The pressure sensors and pressure probes are respectively connected to a controller.

[0006] Furthermore, the mesh cover includes a plurality of concentrically arranged steel wire rings and connecting steel wires radially connected between the plurality of steel wire rings, the steel wire rings and the connecting steel wires forming a mesh structure.

[0007] Furthermore, the pressure probe is fixedly positioned at the intersection of the steel wire loop and the connecting steel wire.

[0008] Furthermore, the outer ring of the mesh cover is fixed with a guide rail, and the scanning rod is fixed with a guide slider, which is slidably connected to the guide rail.

[0009] Furthermore, the mesh cover includes an outer steel wire ring fixedly connected to the housing, and longitudinal and transverse steel wires fixedly arranged inside the outer steel wire ring in a crisscross pattern.

[0010] Furthermore, the pressure probe is fixedly positioned at the intersection of the longitudinal and transverse steel wires.

[0011] Compared with existing technologies, the turbine engine inlet airflow field scanning test device of the present invention has the following advantages:

[0012] (1) The turbine engine intake airflow field scanning test device of the present invention has a pressure probe fixed on the surface of the mesh cover at the air inlet of the engine body, and several pressure sensors are also installed on the scanning rod. By setting the pressure sensors and pressure probes, the total pressure distortion of the intake air in the whole frequency domain can be grasped in a timely manner under the rotation of the scanning rod. Attached Figure Description

[0013] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0014] Figure 1 This is a schematic diagram of the turbine engine inlet airflow field scanning test device according to an embodiment of the present invention;

[0015] Figure 2 for Figure 1 Enlarged view of section A;

[0016] Figure 3 This is a schematic diagram of the side view of the mesh cover in Embodiment 1 of the present invention;

[0017] Figure 4 This is a schematic diagram of the side view of the mesh cover in Embodiment 2 of the present invention.

[0018] Explanation of reference numerals in the attached figures:

[0019] 1-Casing, 2-Fixed bracket, 3-Fan shaft, 4-Fan blade, 5-Fence cover, 6-Scanning rod, 7-Pressure probe, 51-Steel wire ring, 52-Steel wire, 53-Guide rail, 61-Guide slider, 51A-Outer steel wire ring, 52A-Longitudinal steel wire, 53A-Transverse steel wire. Detailed Implementation

[0020] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0021] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0022] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0023] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0024] A turbine engine inlet airflow field scanning test device, such as Figures 1 to 4 As shown, the system includes a housing 1 and an internal mounting bracket 2 and a fan shaft 3. The fan shaft 3 is rotatably connected to the mounting bracket 2. A fan blade 4 is fixedly mounted circumferentially on the fan shaft 3, then passes through a mesh cover 5 and is followed by a scanning rod 6. Several pressure sensors are mounted on the scanning rod 6. The mesh cover 5 is installed at the air inlet of the housing 1, and pressure probes 7 are fixed to the surface of the mesh cover 5. When the fan shaft 3 rotates, it drives the scanning rod 6 to rotate, causing the pressure sensors and pressure probes 7 to work together to detect the full-frequency intake total pressure distortion. The pressure sensors and pressure probes 7 are respectively connected to a controller. The controller can be an external controller or the engine's main controller.

[0025] Example 1: The mesh cover 5 includes a plurality of concentrically arranged steel wire rings 51 and connecting steel wires 52 radially connected between the plurality of steel wire rings 51. The steel wire rings 51 and the connecting steel wires 52 constitute a mesh structure.

[0026] The pressure probe 7 is fixedly installed at the intersection of the steel wire ring 51 and the connecting steel wire 52.

[0027] The outer ring of the mesh cover 5 is fixed with a guide slide rail 53, and the scanning rod 6 is fixed with a guide slider 61. The guide slider 61 is slidably connected to the guide slide rail 53. When the scanning rod 6 rotates, the guide slider 61 rotates inside the guide slide rail 53 to support the scanning rod 6 and prevent the scanning rod 6 from scraping the pressure probe 7.

[0028] Example 2: The mesh cover 5 includes an outer steel wire ring 51A fixedly connected to the housing 1, and longitudinal steel wires 52A and transverse steel wires 53A fixedly arranged in a crisscross pattern inside the outer steel wire ring 51A. The pressure probe 7 is fixedly arranged at the intersection of the longitudinal steel wires 52A and the transverse steel wires 53A.

[0029] Working principle of a turbine engine inlet airflow field scanning test device:

[0030] The air blows the fan blades 4 from the air inlet, which in turn drive the fan shaft 3 to rotate. When the fan shaft 3 rotates, it drives the scanning rod 6 to rotate. The guide slider 61 rotates within the guide rail 53 to support the scanning rod 6 and prevent it from scraping the pressure probe 7. The pressure sensor on the scanning rod 6 and the pressure probe 7 work together to detect the total intake pressure distortion in the full frequency domain and transmit the collected signal to the controller.

[0031] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A turbine engine inlet flow field scanning test apparatus, characterized by: The fan shaft is rotationally connected with the fixing frame, and the fan shaft is fixedly installed with fan blades penetrating through the mesh cover and then installed with a scanning rod, a plurality of pressure sensors are installed on the scanning rod, the air inlet of the casing is installed with the mesh cover, the surface of the mesh cover is fixed with a pressure probe, the scanning rod is driven to rotate when the fan shaft rotates, the pressure sensor and the pressure probe cooperate to detect the total pressure distortion of the full frequency domain, and the pressure sensor and the pressure probe are respectively signal-connected to a controller. The mesh cover comprises an outer steel wire ring fixedly connected with the casing and longitudinally and transversely intersecting longitudinal steel wires and transverse steel wires fixedly arranged in the outer steel wire ring, and the pressure probe is fixedly arranged at the intersection of the longitudinal steel wires and the transverse steel wires. Or the mesh cover comprises a plurality of steel wire rings arranged concentrically and connecting steel wires radially connected between the plurality of steel wire rings, the steel wire rings and the connecting steel wires form a mesh structure, and the pressure probe is fixedly arranged at the intersection of the steel wire rings and the connecting steel wires.

2. A turbine engine inlet flow field scan testing apparatus as defined in claim 1, wherein: The outer ring of the mesh cover is fixed with a guide sliding rail, the scanning rod is fixed with a guide sliding block, and the guide sliding block is slidingly connected with the guide sliding rail.

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