A method for measuring the total pressure at the inlet of a low-pressure turbine guide vane in an aero-engine

Abstract

This application provides a method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine. When applied to the flow function test of a low-pressure turbine guide vane of an aero-engine, the multi-point arc-shaped total pressure rake at the total pressure measurement section at the inlet of the low-pressure turbine guide vane is removed. The corresponding isentropic Mach number at the outlet of the rectifier blade is calculated by measuring the total pressure at the inlet of the rectifier blade and the static pressure on the inner and outer walls of the guide vane inlet. Based on the fitting relationship between the isentropic Mach number at the outlet of the rectifier blade and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient of the rectifier blade is obtained. Then, the corresponding total pressure at the inlet of the rectifier blade and the total pressure recovery coefficient of the rectifier blade are used to calculate the corresponding total pressure at the inlet of the guide vane. There is no interference at the total pressure measurement section at the inlet of the low-pressure turbine guide vane, which can ensure the accuracy of the flow function test of the low-pressure turbine guide vane.

Description

Technical Field

[0001] This application belongs to the field of methods for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, and specifically relates to a method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine. Background Technology

[0002] The flow function test of the low-pressure turbine guide vane of an aero-engine requires measuring the total pressure at the inlet of the low-pressure turbine guide vane.

[0003] In low-pressure turbines of aero engines, considering that the guide vane inlet is generally a non-axial intake, a rectifier blade is added in front of the guide vane in order to provide the inlet airflow angle of the guide vane. The total pressure measurement section of the guide vane inlet is located between the rectifier blade and the guide vane.

[0004] Currently, when conducting flow function tests on low-pressure turbine guide vanes for aero-engines, multiple comb-shaped total pressure pipes are often arranged at the total pressure measurement section at the guide vane inlet to measure the total pressure at the low-pressure turbine guide vane inlet. However, the multi-point comb-shaped total pressure pipes will significantly interfere with the flow field at the guide vane inlet, affecting the accuracy of the flow function test of the low-pressure turbine guide vane. This problem is particularly prominent when the Mach number at the guide vane inlet is high.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A method for measuring the total pressure at the inlet of a low-pressure turbine guide vane in an aero-engine, comprising:

[0010] A CFD model of a low-pressure turbine is constructed, and the radial distribution of the circumferential average airflow angle at the total pressure measurement section of the guide vane inlet is calculated under the isentropic Mach number state at the design outlet of the rectifier blade.

[0011] Multiple comb-shaped total pressure tubes are arranged at the total pressure measurement section at the inlet of the low-pressure turbine rectifier blade to measure the total pressure at the inlet of the rectifier blade. ;

[0012] At the total pressure measurement section at the inlet of the low-pressure turbine guide vane, multiple arc-shaped total pressure rakes are arranged. The probes of these rakes are aligned with the circumferential average airflow angle to measure the total pressure at the guide vane inlet. And to measure the static pressure on the inner and outer walls of the guide vane inlet by drilling holes in the inner and outer walls of the guide vane inlet. ;

[0013] A blowing test was conducted on a low-pressure turbine under multiple rectifier blade outlet isentropic Mach number conditions. The total pressure at the rectifier blade inlet Static pressure on the inner and outer walls of the guide vane inlet The calculation was obtained, and the total pressure at the rectifier blade inlet was used as the basis. Total pressure at the guide vane inlet The isentropic Mach number of each outlet for the rectifier blades was calculated. The total pressure recovery coefficient σ;

[0014] The isentropic Mach number at the outlet of each rectifier blade By performing polynomial curve fitting with the total pressure recovery coefficient σ of the rectifier blade, the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient is obtained;

[0015] The multi-point arc-shaped total pressure rake at the total pressure measurement section of the low-pressure turbine guide vane inlet was removed, and the total pressure at the rectifier blade inlet was measured. Static pressure on the inner and outer walls of the guide vane inlet The corresponding isentropic Mach number at the rectifier blade exit was calculated. Based on the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient σ of the rectifier blade is obtained. Then, the total pressure recovery coefficient σ at the rectifier blade inlet is used... The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. .

[0016] According to at least one embodiment of this application, in the above-described method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, the distance between the measuring section of the total pressure at the inlet of the low-pressure turbine rectifier blade and the leading edge of the rectifier blade is 1.5b, where b is the chord length of the rectifier blade.

[0017] The distance between the total pressure measurement section at the inlet of the low-pressure turbine guide vane and the trailing edge of the rectifier blade is 0.7 bsin. ,in, The outlet configuration angle of the rectifier blade.

[0018] According to at least one embodiment of this application, in the above-described method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, the isentropic Mach number at the outlet of the rectifier blade is... The total pressure at the rectifier blade inlet Static pressure on the inner and outer walls of the guide vane inlet The calculation yields the following results:

[0019] ;

[0020] in,

[0021] It is the isentropic exponent.

[0022] According to at least one embodiment of this application, in the above-described method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, the total pressure at the inlet of the rectifier blade is used as the reference. Total pressure at the guide vane inlet The isentropic Mach number of each outlet for the rectifier blades was calculated. The total pressure recovery coefficient σ is specifically:

[0023] .

[0024] According to at least one embodiment of this application, in the above-described method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, the total pressure at the inlet of the rectifier blade is utilized. The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. Specifically:

[0025] .

[0026] This application has at least the following beneficial technical effects:

[0027] This paper provides a method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine. When applying this method to the flow function test of a low-pressure turbine guide vane of an aero-engine, the multi-point arc-shaped total pressure rake at the total pressure measurement section of the low-pressure turbine guide vane inlet is removed, and the total pressure at the inlet of the rectifier blade is measured. Static pressure on the inner and outer walls of the guide vane inlet The corresponding isentropic Mach number at the rectifier blade exit is obtained. Based on the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient σ of the rectifier blade is obtained. Then, the total pressure recovery coefficient σ at the rectifier blade inlet is used... The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. There is no interference at the total pressure measurement section at the inlet of the low-pressure turbine guide vane, which can ensure the accuracy of the flow function test of the low-pressure turbine guide vane. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the total pressure measurement section at the inlet of the rectifier blade and the total pressure measurement section at the inlet of the guide vane in a low-pressure turbine of an aero-engine, provided in an embodiment of this application.

[0029] Figure 2 This is a schematic diagram of the radial distribution of the circumferential average airflow angle of the total pressure measurement section at the inlet of the low-pressure turbine guide vane of an aero-engine, provided in an embodiment of this application.

[0030] Figure 3 This is a schematic diagram of the structure of the multi-point arc-shaped total pressure rake provided in the embodiments of this application;

[0031] Figure 4 This is a schematic diagram of the fitting relationship curve between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient provided in the embodiments of this application.

[0032] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0033] 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. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0034] 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.

[0035] 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.

[0036] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0037] A method for measuring the total pressure at the inlet of a low-pressure turbine guide vane in an aero-engine, comprising:

[0038] Step 1: Construct a low-pressure turbine CFD model and calculate the radial distribution of the circumferential average airflow angle at the total pressure measurement section of the guide vane inlet under the isentropic Mach number state at the design outlet of the rectifier blade.

[0039] Step 2: Arrange multiple comb-shaped total pressure tubes at the total pressure measurement section at the inlet of the low-pressure turbine rectifier blade to measure the total pressure at the inlet of the rectifier blade. .

[0040] The total pressure measurement section at the inlet of the low-pressure turbine rectifier blade is 1.5b from the leading edge of the rectifier blade, where b is the mid-chord length of the rectifier blade. (See [reference]). Figure 1 Section 0-0.

[0041] The total pressure at the rectifier blade inlet was measured using a multi-point comb-shaped total pressure tube. , with at least 4 branches evenly distributed in the circumference.

[0042] The radial arrangement of the multi-point comb-shaped total pressure tubes at the total pressure measurement section at the rectifier blade inlet adopts the equal ring area method. When the channel height is 20-30mm, 3 points are taken; when the channel height is 30-50mm, 3-5 points are taken; when the channel height is 50-100mm, 5-7 points are taken; and when the channel height is 100-150mm, 7-9 points are taken.

[0043] Step 3: At the total pressure measurement section at the inlet of the low-pressure turbine guide vane, arrange multiple arc-shaped total pressure rakes. The probes of these rakes should be aligned with the circumferential average airflow angle to measure the total pressure at the guide vane inlet. And to measure the static pressure on the inner and outer walls of the guide vane inlet by drilling holes in the inner and outer walls of the guide vane inlet. .

[0044] The distance between the total pressure measurement section at the inlet of the low-pressure turbine guide vane and the trailing edge of the rectifier blade is 0.7 bsin. ,in, For the outlet configuration angle of the rectifier blade, see [reference]. Figure 1 Section 1-1.

[0045] Measure the total pressure at the guide vane inlet using a multi-point arc-shaped total pressure rake. The radial arrangement of the multi-point arc-shaped total pressure rake measuring points adopts the equal ring area method. When the channel height is 20-30mm, the number of multi-point arc-shaped total pressure rakes is 3; when the channel height is 30-50mm, the number of multi-point arc-shaped total pressure rakes is 3-5; when the channel height is 50-100mm, the number of multi-point arc-shaped total pressure rakes is 5-7; and when the channel height is 100-150mm, the number of multi-point arc-shaped total pressure rakes is 7-9. Each multi-point arc-shaped total pressure rake has no less than 5 measuring points, and the circumferential coverage of the central angle range is 360 / n, where n is the number of rectifier blades. The measuring points are evenly distributed circumferentially, and the central angle range between two adjacent measuring points is no greater than 1°. The probe direction is aligned with the circumferential average airflow angle at the corresponding height of the total pressure measurement section at the guide vane inlet.

[0046] Drill holes in the inner and outer walls of the guide vane inlet to measure the static pressure on the inner and outer walls. The static pressure measurement points on the inner and outer walls should be distributed circumferentially and include the wake region and main flow region behind the rectifier blades, with no less than 8 points in each region.

[0047] Step 4: Conduct a blowing test on the low-pressure turbine under isentropic Mach number conditions at the outlet of multiple rectifier blades.

[0048] During the blowing test, the isentropic Mach number at the rectifier blade outlet is uniformly selected within the range of isentropic Mach numbers at the rectifier blade outlet, with at least 8 points selected, including the maximum and minimum isentropic Mach numbers at the outlet.

[0049] Isentropic Mach Number at the rectifier blade exit The total pressure at the rectifier blade inlet Static pressure on the inner and outer walls of the guide vane inlet The calculation yielded:

[0050] ;

[0051] in,

[0052] It is the isentropic exponent.

[0053] Total pressure at the rectifier blade inlet Total pressure at the guide vane inlet The isentropic Mach number of each outlet for the rectifier blades was calculated. Total pressure recovery coefficient σ:

[0054] .

[0055] Step 5: Calculate the isentropic Mach number at the outlet of each rectifier blade. By performing polynomial curve fitting with the total pressure recovery coefficient σ of the rectifier blade, the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient can be obtained. Specifically, the least squares method can be used for fitting.

[0056] Step 6: Remove the multi-point arc-shaped total pressure rake at the total pressure measurement section of the low-pressure turbine guide vane inlet, and measure the total pressure at the rectifier blade inlet. Static pressure on the inner and outer walls of the guide vane inlet The corresponding isentropic Mach number at the rectifier blade exit was calculated. Based on the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient σ of the rectifier blade is obtained. Then, the total pressure recovery coefficient σ at the rectifier blade inlet is used... The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. :

[0057] .

[0058] In one specific embodiment, the aero-engine low-pressure turbine has 85 rectifier blades and 16 guide vanes. The inlet height of the rectifier blades and guide vanes is 82.5 mm, the mid-chord length of the rectifier blades is 44.93 mm, the outlet configuration angle of the rectifier blades is 54.1°, and the isentropic Mach number at the outlet of the rectifier blades is... The range is 0.29~0.50, and the designed outlet isentropic Mach number is 0.44. The process for measuring the total pressure at the guide vane inlet is as follows:

[0059] a) Construct a low-pressure turbine CFD model. Under the condition of an isentropic Mach number of 0.44 at the design outlet of the rectifier blades, calculate the radial distribution of the circumferential average airflow angle at the total pressure measurement section of the guide vane inlet. The results are as follows: Figure 2 As shown.

[0060] b) Arrange multiple comb-shaped total pressure tubes at the total pressure measurement section at the inlet of the low-pressure turbine rectifier blade to measure the total pressure at the inlet of the rectifier blade. .

[0061] The distance between the total pressure measurement section at the inlet of the low-pressure turbine rectifier blade and the leading edge of the rectifier blade is 1.5 * 44.93 = 67.40 mm.

[0062] The total pressure at the rectifier blade inlet was measured using a multi-point comb-shaped total pressure tube. Four branches are evenly distributed around the perimeter.

[0063] The radial arrangement of the multi-point comb-shaped total pressure tubes at the total pressure measurement section at the rectifier blade inlet adopts the equal ring area method, with a measurement point count of 6.

[0064] c) At the total pressure measurement section at the inlet of the low-pressure turbine guide vane, arrange multiple arc-shaped total pressure rakes. The probes of the multiple arc-shaped total pressure rakes are aligned with the circumferential average airflow angle to measure the total pressure at the guide vane inlet. And to measure the static pressure on the inner and outer walls of the guide vane inlet by drilling holes in those walls. .

[0065] The distance between the total pressure measurement section at the inlet of the low-pressure turbine guide vane and the trailing edge of the rectifier blade is 0.7*44.93*sin54.1︒=25.48mm.

[0066] Measure the total pressure at the guide vane inlet using a multi-point arc-shaped total pressure rake. There are 6 multi-point arc-shaped total pressure rakes, and each multi-point arc-shaped total pressure rake has 7 measuring points. The circumferential coverage of the central angle range is 360 / 85=4.2°. The measuring points are evenly distributed circumferentially, and the central angle between two adjacent measuring points is 0.6°. The probe of the multi-point arc-shaped total pressure rake is aligned with the circumferential average airflow angle at the corresponding height of the total pressure measurement section at the guide vane inlet.

[0067] Drill holes in the inner and outer walls of the guide vane inlet to measure the static pressure on the inner and outer walls. The static pressure measurement points on the inner and outer walls are 8 points each, considering the circumferential distribution and the wake and main flow regions behind the rectifier blades.

[0068] Multi-point arc-shaped total pressure rake structure, such as Figure 3 As shown.

[0069] d) Conduct a blowing test on the low-pressure turbine under isentropic Mach number conditions at the outlet of multiple rectifier blades.

[0070] In the blowing test, the isentropic Mach number at the outlet of the rectifier blade was uniformly selected at 8 points within the range of 0.29 to 0.50, namely 0.29, 0.32, 0.35, 0.38, 0.41, 0.44, 0.47, and 0.50.

[0071] Isentropic Mach Number at the rectifier blade exit The total pressure at the rectifier blade inlet Static pressure on the inner and outer walls of the guide vane inlet The calculation yielded:

[0072] ;

[0073] in,

[0074] It is the isentropic exponent.

[0075] Total pressure at the rectifier blade inlet Total pressure at the guide vane inlet The isentropic Mach number of each outlet for the rectifier blades was calculated. Total pressure recovery coefficient σ:

[0076] .

[0077] e) Using the least squares method, determine the isentropic Mach number at the outlet of each rectifier blade. By performing polynomial curve fitting with the total pressure recovery coefficient σ of the rectifier blade, the fitting relationship between the isentropic Mach number at the rectifier blade exit and the total pressure recovery coefficient is obtained:

[0078] σ=-4.9683• +7.2636• -4.0306• +0.9576• +0.9138;

[0079] The fitting curve of the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient is shown in the figure. Figure 4 As shown.

[0080] f) Remove the multi-point arc-shaped total pressure rake at the total pressure measurement section of the low-pressure turbine guide vane inlet, and measure the total pressure at the rectifier blade inlet. Static pressure on the inner and outer walls of the guide vane inlet The corresponding isentropic Mach number at the rectifier blade exit was calculated. Based on the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient σ of the rectifier blade is obtained. Then, the total pressure recovery coefficient σ at the rectifier blade inlet is used... The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. :

[0081] .

[0082] When applying the method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, as disclosed in the above embodiments, to the flow function test of the low-pressure turbine guide vane of an aero-engine, the multi-point arc-shaped total pressure rake at the total pressure measurement section at the inlet of the low-pressure turbine guide vane is removed, and the total pressure at the inlet of the rectifier blade is measured. Static pressure on the inner and outer walls of the guide vane inlet The corresponding isentropic Mach number at the rectifier blade exit was calculated. Based on the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient σ of the rectifier blade is obtained. Then, the total pressure recovery coefficient σ at the rectifier blade inlet is used... The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. There is no interference at the total pressure measurement section at the inlet of the low-pressure turbine guide vane, which can ensure the accuracy of the flow function test of the low-pressure turbine guide vane.

[0083] 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 total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine, characterized in that, include: A CFD model of a low-pressure turbine is constructed, and the radial distribution of the circumferential average airflow angle at the total pressure measurement section of the guide vane inlet is calculated under the isentropic Mach number state at the design outlet of the rectifier blade. Multiple comb-shaped total pressure tubes are arranged at the total pressure measurement section at the inlet of the low-pressure turbine rectifier blade to measure the total pressure at the inlet of the rectifier blade. ; At the total pressure measurement section at the inlet of the low-pressure turbine guide vane, multiple arc-shaped total pressure rakes are arranged. The probes of these rakes are aligned with the circumferential average airflow angle to measure the total pressure at the guide vane inlet. And to measure the static pressure on the inner and outer walls of the guide vane inlet by drilling holes in the inner and outer walls of the guide vane inlet. ; A blowing test was conducted on a low-pressure turbine under multiple rectifier blade outlet isentropic Mach number conditions. The total pressure at the rectifier blade inlet Static pressure on the inner and outer walls of the guide vane inlet The calculation was obtained, and the total pressure at the rectifier blade inlet was used as the basis. Total pressure at the guide vane inlet The isentropic Mach number of each outlet for the rectifier blades was calculated. The total pressure recovery coefficient σ; The isentropic Mach number at the outlet of each rectifier blade By performing polynomial curve fitting with the total pressure recovery coefficient σ of the rectifier blade, the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient is obtained; The multi-point arc-shaped total pressure rake at the total pressure measurement section of the low-pressure turbine guide vane inlet was removed, and the total pressure at the rectifier blade inlet was measured. Static pressure on the inner and outer walls of the guide vane inlet The corresponding isentropic Mach number at the rectifier blade exit was calculated. Based on the fitting relationship between the isentropic Mach number at the rectifier blade outlet and the total pressure recovery coefficient, the corresponding total pressure recovery coefficient σ of the rectifier blade is obtained. Then, the total pressure recovery coefficient σ at the rectifier blade inlet is used... The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. .

2. The method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine according to claim 1, characterized in that, The distance between the inlet total pressure measurement section of the low-pressure turbine rectifier blade and the leading edge of the rectifier blade is 1.5b, where b is the chord length of the rectifier blade. The distance between the total pressure measurement section at the inlet of the low-pressure turbine guide vane and the trailing edge of the rectifier blade is 0.7 bsin. ,in, The outlet configuration angle of the rectifier blade.

3. The method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine according to claim 1, characterized in that, Isentropic Mach Number at the rectifier blade exit The total pressure at the rectifier blade inlet Static pressure on the inner and outer walls of the guide vane inlet The calculation yields the following results: ； in, It is the isentropic exponent.

4. The method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine according to claim 1, characterized in that, Total pressure at the rectifier blade inlet Total pressure at the guide vane inlet The isentropic Mach number of each outlet for the rectifier blades was calculated. The total pressure recovery coefficient σ is specifically: 。 5. The method for measuring the total pressure at the inlet of a low-pressure turbine guide vane of an aero-engine according to claim 1, characterized in that, Utilizing the total pressure at the rectifier blade inlet The total pressure recovery coefficient σ of the rectifier blades is calculated to obtain the corresponding total pressure at the guide vane inlet. Specifically: 。

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