A method for correcting aerodynamic parameters of fan component test outlet considering intake distortion

Abstract

This invention provides a method for correcting aerodynamic parameters at the fan component outlet during test, taking into account intake distortion. This method constructs a database of aerodynamic parameters generated during uniform flow tests by rationally arranging outlet measurement probes. During intake distortion tests, these aerodynamic parameters are corrected to obtain more accurate average aerodynamic parameters at the fan outlet. The aerodynamic parameters obtained using this method can accurately calculate fan component characteristics such as pressure ratio and efficiency under intake distortion conditions, providing data support for aircraft engine performance evaluation.

Description

Technical Field

[0001] The invention belongs to the field of aero-engine design, and in particular relates to a method for correcting aerodynamic parameters of a fan component test outlet taking into account intake distortion. Background Art

[0002] The operating environment of aircraft engines is relatively harsh. Fan components usually work under a distorted flow field with uneven distribution of inlet total pressure. It is necessary to obtain the average aerodynamic parameters such as outlet total pressure and total temperature under inlet distortion in fan component tests. For fan component tests under inlet distortion, it is necessary to arrange total pressure and total temperature probes at the outlet section to obtain the distribution of aerodynamic parameters such as total pressure and total temperature. In order to obtain the aerodynamic parameter distribution of the fan component outlet section as accurately as possible, it is hoped that more measurement points will be used. However, when measuring at multiple points, the probe has a greater impact on the airflow field and will produce a significant blocking effect. Usually, 6 to 8 total pressure and total temperature composite probes are arranged at the fan outlet to obtain aerodynamic parameters. The current measurement method cannot comprehensively consider the influence of the upstream fan blade wake and the uneven distribution of aerodynamic parameters caused by inlet distortion. The correction method for fan outlet aerodynamic parameters under inlet distortion in the journal "Analysis and Correction of Fan Inlet Pressure Distortion Test Performance" (Gas Turbine Test and Research, 2017(04):16-22) only considers circumferential averaging. Although the influence of inlet distortion is considered, the influence of upstream blade wake cannot be considered. The method for measuring outlet aerodynamic parameters in the aviation industry standard of the People's Republic of China, "Test Method for Aerodynamic Performance of Aviation Gas Turbine Engine Compressors" (HB 7115-2020), only mentions the use of no less than six multi-point probes for measurement, and the uneven factors along the pitch direction should be considered, that is, the influence of the upstream blade wake is considered, but the uneven factors of aerodynamic parameters along the circumferential direction during the intake distortion test are not considered. Summary of the Invention

[0003] In order to solve the above problems, the purpose of the present invention is to provide a method for measuring and correcting the test outlet aerodynamic parameters of fan components under intake distortion conditions, in view of the comprehensive influence of the circumferential unevenness caused by the upstream blade wake and intake distortion on the outlet aerodynamic parameters of fan components.

[0004] To achieve the above-mentioned object, the present invention provides the following technical solution: a method for correcting aerodynamic parameters of a fan component test outlet taking into account intake distortion, the correction method comprising the following steps:

[0005] S1: Install multiple measuring probes at the fan outlet, where the positions of the multiple measuring probes are determined based on the wake of the last-stage stator blades and the inlet distortion;

[0006] S2: Conduct multiple uniform flow fan component tests under different outlet flow conditions to obtain aerodynamic parameters measured by multiple measurement probes, and form a uniform flow database and a functional relationship, wherein the functional relationship is a function of the surface average aerodynamic parameters of the fan outlet cross section under different outlet flow rates and the aerodynamic parameters measured by the multiple measurement probes;

[0007] S3: Conduct fan component tests under intake distortion to obtain aerodynamic parameters measured by multiple measurement probes;

[0008] S4: Based on the uniform flow database and functional relationship obtained in S2, the aerodynamic parameters obtained in S3 are corrected to obtain the surface average aerodynamic parameters of the fan component outlet cross section under intake distortion.

[0009] The method for correcting aerodynamic parameters of a fan component test outlet taking into account intake distortion provided by the present invention also has the following characteristics: the number of probes at the fan outlet position is not less than 6, the phase angles of each probe at the fan outlet position relative to the upstream last-stage stator blades are different, the phase angle difference between two adjacent probes relative to the corresponding upstream last-stage stator blades is the same, and at least one probe is located in the middle position of the upstream last-stage stator blade channel.

[0010] The method for correcting aerodynamic parameters of a fan component test outlet taking into account intake distortion provided by the present invention also has the characteristic that at least one probe is provided in any 90-degree sector at the fan outlet.

[0011] The method for correcting aerodynamic parameters of a fan component test outlet considering intake distortion provided by the present invention further has the following characteristics: the surface average aerodynamic parameters of the fan outlet cross section under the uniform flow are:

[0012]

[0013]

[0014] Among them, P i Total pressure at fan outlet under uniform flow, T i Total temperature, where i represents the data of the i-th probe and n is the total number of probes at the fan outlet.

[0015] The method for correcting aerodynamic parameters of a fan component test outlet considering intake distortion provided by the present invention further has the following characteristics: the functional relationship in S2 is:

[0016]

[0017] The method for correcting aerodynamic parameters of a fan component test outlet considering intake distortion provided by the present invention further has the following characteristics: the correction in S4 comprises the following steps:

[0018] S4.1: Based on the functional relationship obtained in S2 and the aerodynamic parameter total pressure P′ measured by a measuring probe under distortion conditions i , total temperature T′ i Calculate the average aerodynamic parameters of the outlet of the inter-blade channel where the measurement probe is located .

[0019] S4.2: Calculate the average aerodynamic parameters of the fan component outlet cross section under inlet distortion based on the circumferential position θ of the inter-blade passage where the different probes are located.

[0020] in θ n+1 =2π+θ1

[0021] in θ n+1 =2π+θ1.

[0022] Beneficial effects

[0023] The present invention provides a method for correcting aerodynamic parameters at the outlet of a fan component test that takes into account intake distortion. By rationally arranging the circumferential positions of outlet measurement probes, a database of aerodynamic parameters of the fan component outlet during a uniform flow test is constructed. The aerodynamic parameters of the fan outlet are corrected during the intake distortion test. This method can capture the circumferential non-uniformity of aerodynamic parameters caused by intake distortion and the impact of fan blade wakes on the downstream, thereby obtaining more accurate average aerodynamic parameters of the fan outlet surface. The aerodynamic parameters obtained by this method can accurately calculate the pressure ratio, efficiency, and other characteristics of the fan component under intake distortion conditions, providing data support for the performance evaluation of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0025] Figure 1 A flow chart of a method for correcting fan component characteristics considering intake distortion provided by an embodiment of the present invention;

[0026] Figure 2 Schematic diagram of the fan outlet probe layout and calculation method for uniform flow;

[0027] Figure 3 Schematic diagram of the fan outlet probe layout and calculation method under intake distortion. DETAILED DESCRIPTION

[0028] The present invention is further described in detail below with reference to the accompanying drawings and examples. However, it should be noted that these embodiments are not limitations of the present invention, and any equivalent transformations or substitutions in functions, methods, or structures made by ordinary technicians in this field based on these embodiments are within the scope of protection of the present invention.

[0029] In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the invention.

[0030] Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified with "first," "second," etc., may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0031] The terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediary; and internal communication between two components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0032] like Figure 1-3 As shown, an embodiment of the present invention provides a method for correcting aerodynamic parameters of a fan component test outlet taking into account intake distortion, the correction method comprising the following steps:

[0033] S1: Install multiple measuring probes at the fan outlet, where the positions of the multiple measuring probes are determined based on the wake of the last-stage stator blades and the inlet distortion;

[0034] S2: If Figure 2 , conducting multiple uniform flow fan component tests under different outlet flow conditions, obtaining aerodynamic parameters measured by multiple measurement probes, forming a uniform flow database and a functional relationship, wherein the functional relationship is a function of the surface average aerodynamic parameters of the fan outlet cross section under different outlet flow rates and the aerodynamic parameters measured by multiple measurement probes;

[0035] S3: Conduct fan component tests under intake distortion to obtain aerodynamic parameters measured by multiple measurement probes; adjust different intake distortion levels and different fan test conditions to obtain the aerodynamic parameters of each probe at the fan outlet under different test conditions;

[0036] S4: As Figure 3 , based on the uniform flow database and functional relationship obtained by S2, the aerodynamic parameters obtained by S3 are corrected to obtain the surface average aerodynamic parameters of the fan component outlet section under intake distortion.

[0037] In some embodiments, the number of probes at the fan outlet position is not less than 6, the phase angle of each probe at the fan outlet position relative to the upstream last-stage stator blade is different, the phase angle difference between two adjacent probes relative to the corresponding upstream last-stage stator blade is the same, and at least one probe is located in the middle position of the upstream last-stage stator blade channel.

[0038] In some embodiments, at least one probe is provided in any 90-degree sector at the fan outlet. To account for the effect of inlet distortion on the aerodynamic parameters of the fan outlet, the outlet probes should be relatively evenly distributed at all circumferential angles of the outlet.

[0039] In some embodiments, the surface average aerodynamic parameters of the fan outlet cross section under the uniform flow are:

[0040]

[0041]

[0042] Among them, P i Total pressure at fan outlet under uniform flow, T i Total temperature, where i represents the data of the i-th probe, n is the total number of fan outlet probes, α i is the phase angle of the i-th probe relative to the upstream last-stage stator blade and α i -α i-1 =α1-α n Is a fixed value.

[0043] In some embodiments, the functional relationship in S2 is:

[0044]

[0045] In some embodiments, the modification in S4 includes the following steps:

[0046] S4.1: Based on the functional relationship obtained in S2 and the aerodynamic parameter total pressure P′ measured by a measuring probe under distortion conditions i , total temperature T′ i Calculate the average aerodynamic parameters of the outlet of the inter-blade channel where the measurement probe is located

[0047] S4.2: Calculate the average aerodynamic parameters of the fan component outlet cross section under inlet distortion based on the circumferential position θ of the inter-blade passage where the different probes are located.

[0048] in θ n+1 =2π+θ1

[0049] in θ n+1 =2π+θ1.

[0050] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention. The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and variations without departing from the technical principles of the present invention, and such improvements and variations shall also be considered within the scope of protection of the present invention.

Claims

1. A method for correcting aerodynamic parameters of a fan component test outlet considering intake distortion, characterized in that: The correction method comprises the following steps: S1: Install multiple measuring probes at the fan outlet, where the positions of the multiple measuring probes are determined based on the wake of the last-stage stator blades and the inlet distortion; S2: Conduct multiple uniform flow fan component tests under different outlet flow conditions to obtain aerodynamic parameters measured by multiple measurement probes, and form a uniform flow database and a functional relationship, wherein the functional relationship is a function of the surface average aerodynamic parameters of the fan outlet cross section under different outlet flow rates and the aerodynamic parameters measured by the multiple measurement probes; S3: Conduct fan component tests under intake distortion to obtain aerodynamic parameters measured by multiple measurement probes; S4: Based on the uniform flow database and function relationship obtained in S2, the aerodynamic parameters obtained in S3 are corrected to obtain the surface average aerodynamic parameters of the fan component outlet section under intake distortion. The surface average aerodynamic parameters of the fan outlet section under the uniform flow are: Among them, P i Total pressure at fan outlet under uniform flow, T i Total temperature, where i represents the data of the i-th probe, and n is the total number of fan outlet probes. The correction in S4 includes the following steps: S4.1: Based on the functional relationship obtained in S2 and the aerodynamic parameter total pressure P measured by a measuring probe under distortion conditions i ′, total temperature T i 'Calculate the average aerodynamic parameters of the outlet of the inter-blade channel where the measurement probe is located S4.2: Calculate the average aerodynamic parameters of the fan component outlet cross section under inlet distortion based on the circumferential position θ of the inter-blade passage where the different probes are located. among them i n+1 =2π+θ1 among them i n+1 = 2π+θ1.

2. The method for correcting aerodynamic parameters of a fan component test outlet considering intake distortion according to claim 1 is characterized in that: The number of probes at the fan outlet position is not less than 6. The phase angle of each probe at the fan outlet position relative to the upstream last-stage stator blade is different. The phase angle difference between two adjacent probes relative to the corresponding upstream last-stage stator blade is the same. At least one probe is located in the middle position of the upstream last-stage stator blade channel.

3. The method for correcting aerodynamic parameters of a fan component test outlet considering intake distortion according to claim 2, characterized in that: There is at least one probe in any 90-degree sector at the fan outlet.

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