Method for measuring flow field at outlet of compressor under environment of whole aero-engine and core engine

Abstract

The application belongs to the technical field of compressor outlet flow field measurement under the environment of aero-engine whole machine and core machine, and particularly relates to a kind of compressor outlet flow field measurement method under the environment of aero-engine whole machine and core machine, comprising: temperature sensor or pressure sensor is arranged at the leading edge of the strut at the inlet of the combustion chamber, the lead line of the temperature sensor and the pressure sensor is led out through the strut; according to the principle of maximum coverage of measuring points, the distribution of the temperature sensor and the pressure sensor on the strut is determined according to the relative circumferential position of the strut at the inlet of the combustion chamber and the adjacent blade at the outlet of the compressor; the temperature and pressure measured by the temperature sensor and the pressure sensor are arranged in one grid according to the relative circumferential position of the strut at the inlet of the combustion chamber and the blade at the outlet of the compressor, and expanded to all grids to obtain the compressor outlet flow field.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of measuring the flow field at the outlet of a compressor in the environment of an aero-engine whole machine and a core machine, and particularly relates to a method for measuring the flow field at the outlet of a compressor in the environment of an aero-engine whole machine and a core machine. BACKGROUND

[0002] Currently, the measurement of the flow field at the outlet of a compressor in the environment of an aero-engine whole machine and a core machine is mainly based on the following two technical solutions:

[0003] 1) A sensor is arranged between the outlet of the compressor and the inlet of the combustion chamber to measure the flow field at the outlet of the compressor. In this technical solution, the measurement sensor will interfere with the flow field at the inlet of the combustion chamber, increase the unevenness of the flow field at the inlet of the combustion chamber, cause local hot spots in the airflow of the combustion chamber, and ablate the turbine hot pieces, which has a great safety hazard. Moreover, as the axial size of the aero-engine is gradually reduced, the connection between the compressor and the combustion chamber is more compact, and the space between the outlet of the compressor and the inlet of the combustion chamber is narrow, making it difficult to arrange the sensor.

[0004] 2) A sensor is arranged in the blade passage at the outlet of the compressor to measure the flow field between the blade passages at the outlet of the compressor. According to the corresponding relationship between the flow field between the blade passages at the outlet of the compressor and the flow field at the outlet section, the flow field at the outlet of the compressor is corrected. However, the working environment of the compressor in the part test is different from that in the aero-engine whole machine and the core machine, and the corresponding relationship between the flow field between the blade passages at the outlet of the compressor and the flow field at the outlet section has deviations in the environment of the aero-engine whole machine and the core machine, which makes it difficult to ensure the accuracy of the measurement results of the flow field between the blade passages at the outlet of the compressor. In addition, the corresponding relationship between the flow field between the blade passages at the outlet of the compressor and the flow field at the outlet section will change with the rotational speed and the pressure ratio. It is difficult to obtain the corresponding relationship between the flow field between the blade passages at the outlet of the compressor and the flow field at the outlet section under the conditions of full rotational speed and full pressure ratio through part test. It is necessary to use test data for interpolation, and it is difficult to ensure the accuracy of the flow field at the outlet of the compressor through correction.

[0005] The present application is proposed in view of the above technical defects.

[0006] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0007] The purpose of the present application is to provide a method for measuring the flow field at the outlet of a compressor in the environment of an aero-engine whole machine and core machine, so as to overcome or alleviate at least one of the technical defects known to exist.

[0008] The technical solution of the present application is:

[0009] A method for measuring the flow field at the outlet of a compressor in the environment of an aero-engine whole machine and core machine, comprising:

[0010] A temperature sensor or a pressure sensor is arranged at the leading edge of the strut at the inlet of the combustion chamber, and the lead wires of the temperature sensor and the pressure sensor are led out through the strut;

[0011] According to the principle of maximizing the coverage of the measuring points on the whole grid distance, the distribution of the temperature sensor and the pressure sensor on the strut is determined according to the relative circumferential position of the strut at the inlet of the combustion chamber and the adjacent blade at the outlet of the compressor;

[0012] The temperature and pressure measured by the temperature sensor and the pressure sensor are arranged in one grid distance according to the relative circumferential position of the strut at the inlet of the combustion chamber and the blade at the outlet of the compressor, and are expanded to all grid distances to obtain the flow field at the outlet of the compressor.

[0013] According to at least one embodiment of the present application, in the above-mentioned method for measuring the flow field at the outlet of a compressor in the environment of an aero-engine whole machine and core machine, the relative circumferential position of the strut at the inlet of the combustion chamber and the adjacent blade at the outlet of the compressor is calculated as follows:

[0014]

[0015]

[0016] Wherein,

[0017] δ i is the relative circumferential position of the i-th strut at the inlet of the combustion chamber and the adjacent blade at the outlet of the compressor;

[0018] alf i is the circumferential angle of the i-th strut at the inlet of the combustion chamber and the adjacent blade at the outlet of the compressor;

[0019] M is the number of struts at the inlet of the combustion chamber;

[0020] N is the number of blades at the outlet of the compressor, and the first strut at the inlet of the combustion chamber and the first blade at the outlet of the compressor are at 0° in the circumferential direction;

[0021] i is the serial number of the strut at the inlet of the combustion chamber;

[0022] K i is the largest integer of .

[0023] According to at least one embodiment of the present application, in the method for measuring the flow field at the outlet of the compressor in the environment of the aero-engine and the core engine, when the number of the vanes at the outlet of the compressor is 87 and the number of the vanes at the inlet of the combustion chamber is 10, the temperature sensors are arranged on the 2nd, 4th, 6th, 8th and 10th vanes at the inlet of the combustion chamber, and the pressure sensors are arranged on the 1st, 3rd, 5th, 7th and 9th vanes at the inlet of the combustion chamber.

[0024] In one pitch, the temperatures measured by the temperature sensors are arranged, and the arrangement is that the temperatures measured by the temperature sensors on the 4th, 10th, 6th, 2nd and 8th vanes at the inlet of the combustion chamber.

[0025] In one pitch, the pressures measured by the pressure sensors are arranged, and the arrangement is that the pressures measured by the pressure sensors on the 1st, 7th, 3rd, 9th and 5th vanes at the inlet of the combustion chamber. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 FIG. 1 is a schematic diagram of the method for measuring the flow field at the outlet of the compressor in the environment of the aero-engine and the core engine provided by the embodiments of the present application;

[0027] Figure 2 FIG. 2 is a schematic diagram of arranging the temperatures measured by the temperature sensors in one pitch provided by the embodiments of the present application;

[0028] Figure 3 FIG. 3 is a schematic diagram of arranging the pressures measured by the pressure sensors in one pitch provided by the embodiments of the present application;

[0029] In the drawings:

[0030] 1-compressor; 2-vane; 3-sensor; 4-vane; 5-combustion chamber.

[0031] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0032] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are used to explain the present application rather than limit the present application. It should be noted that only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0033] 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 terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0034] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral 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; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0035] In the core of an aero-engine, the compressor outlet is connected to the combustion chamber inlet. Blades are installed at the compressor outlet, and a support plate is installed at the combustion chamber inlet. Under uniform intake conditions, the airflow in each blade passage at the compressor outlet is centrally symmetrically distributed periodically. However, due to the wake effect of the airflow within each blade passage, the flow field at the outlet is not uniformly distributed. Based on this, this application provides a method for measuring the compressor outlet flow field under the conditions of the entire aero-engine and its core, including:

[0036] A temperature sensor or pressure sensor is installed at the leading edge of the support plate at the combustion chamber inlet. The leads of the temperature sensor or pressure sensor are led out through the support plate. Specifically, mounting holes are made at the leading edge of the support plate at the combustion chamber inlet for mounting the head of the temperature sensor or pressure sensor, and lead-in channels are made in the support plate to lead out the leads of the temperature sensor or pressure sensor. Figure 1 As shown;

[0037] Based on the principle of maximizing the coverage of the entire grid pitch by measuring points, the distribution of temperature and pressure sensors on the support plate is determined according to the relative circumferential position of the support plate at the combustion chamber inlet and the blades at the outlet of the adjacent compressor.

[0038] The temperature and pressure measured by the temperature and pressure sensors are arranged within a grid spacing according to the relative circumferential positions of the support plate at the combustion chamber inlet and the blades at the compressor outlet, and then extended to the entire grid spacing to obtain the compressor outlet flow field.

[0039] Regarding the compressor outlet flow field measurement method disclosed in the above embodiments for the entire aero-engine and core engine environment, those skilled in the art will understand that its design involves modifying the support plate at the combustion chamber inlet and installing temperature and pressure sensors at the leading edge of the support plate to measure the compressor outlet flow field. The measurement is accurate, and the temperature and pressure sensors can be easily arranged. Furthermore, the leads of the temperature and pressure sensors are routed out from within the support plate, avoiding interference with the combustion chamber inlet flow field. In addition, the design follows the principle of maximizing the coverage of the entire grid spacing by measuring points, based on the relationship between the support plate at the combustion chamber inlet and the phase... The relative circumferential position of the blades at the compressor outlet determines the distribution of temperature and pressure sensors on the support plate. The temperature and pressure measured by the temperature and pressure sensors are arranged within a grid pitch according to the relative circumferential position of the support plate at the combustion chamber inlet and the blades at the compressor outlet. This arrangement is then expanded to the entire grid pitch to obtain the compressor outlet flow field. In other words, the temperature and pressure measured by the circumferentially distributed temperature and pressure sensors are first concentrated within a grid pitch, and then expanded to the entire grid pitch to obtain a periodically distributed compressor outlet flow field, which can improve the accuracy of compressor outlet flow field measurement.

[0040] In some optional embodiments, in the above-described method for measuring the compressor outlet flow field under the conditions of the entire aero-engine and its core, the relative circumferential position of the support plate at the combustion chamber inlet and the blade at the adjacent compressor outlet is calculated as follows:

[0041]

[0042]

[0043] in,

[0044] δ i The relative circumferential position of the i-th support plate at the combustion chamber inlet and the blade at the adjacent compressor outlet;

[0045] alf i The circumferential angle between the i-th support plate at the combustion chamber inlet and the blade at the adjacent compressor outlet;

[0046] M represents the number of support plates at the combustion chamber inlet;

[0047] N represents the number of blades at the compressor outlet. The first support plate at the combustion chamber inlet and the first blade at the compressor outlet are at 0° in the circumferential direction.

[0048] i represents the serial number of the support plate at the combustion chamber inlet;

[0049] K i To make alf i The largest integer less than or equal to 0.

[0050] In some optional embodiments, in the above-described method for measuring the compressor outlet flow field under the conditions of the entire aero-engine and its core, when the number of support plates at the combustion chamber inlet is 10 and the number of blades at the compressor outlet is 87, the temperature sensors are distributed on the 2nd, 4th, 6th, 8th, and 10th support plates, and the pressure sensors are distributed on the 1st, 3rd, 5th, 7th, and 9th support plates, as detailed in the table below:

[0051] i Circumferential position delta i ]] Sensor 1 0 0 Pressure 2 36 0.7 Temperature 3 72 0.4 Pressure 4 108 0.1 Temperature 5 144 0.8 Pressure 6 180 0.5 Temperature 7 216 0.2 Pressure 8 252 0.9 Temperature 9 288 0.6 Pressure 10 324 0.3 Temperature

[0052] The temperatures measured by the temperature sensors are arranged in a grid pattern, specifically the temperatures measured by the temperature sensors on the 4th, 10th, 6th, 2nd, and 8th support plates at the combustion chamber inlet. Figure 2 As shown, the temperature distribution of the flow field within one grid pitch at the compressor outlet can be characterized, with obvious troughs and peaks. Extending this to various grid pitches, the temperature distribution of the flow field at the compressor outlet can be obtained.

[0053] The pressures measured by the pressure sensors are arranged in a grid pattern, specifically the pressures measured by the pressure sensors on the 1st, 7th, 3rd, 9th, and 5th support plates at the combustion chamber inlet. Figure 3 As shown, the pressure distribution of the flow field within one grid pitch at the compressor outlet can be characterized, exhibiting distinct troughs and peaks. Extending this to various grid pitches yields the pressure distribution of the flow field at the compressor outlet.

[0054] The compressor outlet flow field measurement method disclosed in the embodiments of this application for the whole engine and core engine environment has been verified to improve the measurement accuracy of the flow field temperature distribution by 0.8 percentage points over the flow field temperature distribution obtained by the correction method, and the measurement accuracy of the flow field pressure distribution obtained by the method has been verified to improve by 1.2 percentage points over the flow field pressure distribution obtained by the correction method, over the entire speed range.

[0055] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0056] 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 method for measuring the compressor outlet flow field under the conditions of an aero-engine complete unit and core engine, characterized in that, include: A temperature sensor and a pressure sensor are installed at the leading edge of the support plate at the combustion chamber inlet, and the leads of the temperature sensor and the pressure sensor are led out through the support plate. Based on the principle of maximizing the coverage of the entire grid pitch by measuring points, the distribution of temperature and pressure sensors on the support plate is determined according to the relative circumferential position of the support plate at the combustion chamber inlet and the blades at the outlet of the adjacent compressor. The temperature and pressure measured by the temperature sensor and the pressure sensor are arranged within a grid spacing according to the relative circumferential positions of the support plate at the combustion chamber inlet and the blades at the compressor outlet, and then extended to the entire grid spacing to obtain the compressor outlet flow field. The relative circumferential position of the support plate at the combustion chamber inlet and the blade at the outlet of the adjacent compressor is calculated as follows: in, δ i The relative circumferential position of the i-th support plate at the combustion chamber inlet and the blade at the adjacent compressor outlet; alf i The circumferential angle between the i-th support plate at the combustion chamber inlet and the blade at the adjacent compressor outlet; M represents the number of support plates at the combustion chamber inlet; N represents the number of blades at the compressor outlet. The first support plate at the combustion chamber inlet and the first blade at the compressor outlet are at 0° in the circumferential direction. i represents the serial number of the support plate at the combustion chamber inlet; K i In order to make The largest integer.

2. The method for measuring the compressor outlet flow field under the conditions of the entire aero-engine and its core engine as described in claim 1, characterized in that, When the number of support plates at the combustion chamber inlet is 10 and the number of blades at the compressor outlet is 87, the temperature sensors are distributed on the 2nd, 4th, 6th, 8th and 10th support plates, and the pressure sensors are distributed on the 1st, 3rd, 5th, 7th and 9th support plates. The temperatures measured by the temperature sensors are arranged in a grid pattern, specifically the temperatures measured by the temperature sensors on the 4th, 10th, 6th, 2nd, and 8th support plates at the combustion chamber inlet. The pressures measured by the pressure sensors are arranged in a grid pattern, specifically the pressures measured by the pressure sensors on the 1st, 7th, 3rd, 9th, and 5th support plates at the combustion chamber inlet.

Images