CN109372788B - Combined blade type probe measuring method capable of adjusting airflow parameters of stationary blade inlet - Google Patents
Combined blade type probe measuring method capable of adjusting airflow parameters of stationary blade inlet Download PDFInfo
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- CN109372788B CN109372788B CN201811502985.2A CN201811502985A CN109372788B CN 109372788 B CN109372788 B CN 109372788B CN 201811502985 A CN201811502985 A CN 201811502985A CN 109372788 B CN109372788 B CN 109372788B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
Abstract
The invention relates to a combined blade profile probe measuring method for measuring airflow parameters of an interstage adjustable stationary blade inlet of an aviation multistage axial flow compressorWhen the probe is installed, a deflection angle is provided, the direction angle difference theta exists between the probe and a measuring point of a conventional installation leaf-shaped probe, the radial position and the measuring point number of the installation leaf-shaped probe with the deflection angle are the same as those of the conventional installation leaf-shaped probe according to requirements, at least one leaf-shaped probe with deflection angle installation exists at the same radial position, the theta is not more than 20 degrees and is not more than the insensitive angle range α of the leaf-shaped probewAnd not less than 10 degrees, the conventional blade-shaped probe is used for measuring the working condition of more than 90 percent of the relative conversion rotating speed; the blade-shaped probe with the deflection angle is used for measuring the working condition with the relative conversion rotating speed of below 85 percent. The invention effectively avoids the interference of the low-speed blade profile probe on the flow field of the suction surface of the stationary blade, thereby reducing the negative influence of the low-speed blade profile probe on the aerodynamic performance of the compressor.
Description
Technical Field
The invention relates to the field of aerodynamic performance test research of a multistage axial flow compressor of an aeroengine, and provides a combined blade type probe measuring method for accurately measuring airflow parameters of an adjustable stationary blade inlet of the multistage axial flow compressor in a wide working rotating speed variation range.
Background
In order to develop an axial flow compressor part for an aircraft engine with advanced performance, detailed knowledge of internal complex flow information of the axial flow compressor under design working conditions and non-design working conditions is required in a design stage, and experimental measurement is a recognized most effective and reliable technical means for obtaining aerodynamic performance parameters of the axial flow compressor. Due to the fact that the axial-flow compressor rotor and stator blade rows are arranged in a staggered mode, the flow channel space is narrow, the conventional plug-in probe with the support rod cannot well meet the requirement for testing the gas flow parameters between the stages of the compressor, and particularly for small-size compact-structure layout compressor tests, more advanced testing technology needs to be developed to obtain the performance parameters between the stages of the compressor. The blade type probe technology is a more test means adopted in the measurement of the interstage steady-state flow field of the compressor at present. A plurality of blades are selected from blade rows of each stage of stator of the gas compressor as support carriers, and a multi-point probe is embedded on the surface of each blade along the radial direction, so that the blocking and interference effects of the traditional plug-in probe on the interstage flow field are remarkably reduced, the specific values and radial distribution of steady-state pressure and temperature of each stage of rotor outlet of the gas compressor can be truly acquired, and the interstage flow field information of the gas compressor is accurately reflected. In view of the obvious advantages of the leaf-shaped probe technology, in the early 70 th century, leaf-shaped probes have been applied to aviation axial-flow compressor scientific research tests by various main engine companies abroad, and the testing technology is also adopted in multistage axial-flow compressor interstage performance tests in China since the fifteen th period of engine research institute.
For the measurement of the performance parameters of the interstage of the multistage axial-flow compressor, in order to obtain the rear flow parameters of each stage of rotor, except that the blade-shaped probes are not installed on the inlet guide vanes, the blade-shaped probes are generally installed on other stationary vanes. When the adjustable-angle stator blade is adopted by the gas compressor, the installation angle of the stator blade is adjusted along with the change of the working rotating speed of the gas compressor, so that the blade-shaped probe arranged on the adjustable stator blade deflects along with the installation angle, and when the deflection angle exceeds the insensitive angle range, the measurement error of the blade-shaped probe is obviously increased. The axis of the conventional vane-type probe stagnation cover is basically along the angular direction of the inlet geometric structure of the stator vane, the insensitive angular range is generally not more than +/-15 degrees, the rotation angle of the low-rotation-speed adjustable stator vane in the air compressor cannot be adapted, the accuracy of the measurement result of the flow field parameter of the low-rotation-speed rotor in the air compressor is reduced, the requirement of the test measurement precision cannot be met, and the effective evaluation of the full-working-condition aerodynamic performance of the aviation axial flow air compressor is severely restricted. At present, aiming at solving the problem that the insensitive angle range of the blade-shaped probe on the adjustable stationary blade of the multistage axial flow compressor is limited, the introduction of related technologies and methods is not found through the approaches of technical novelty retrieval, literature retrieval and the like.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the problem that the insensitive angle range of a blade-shaped probe on an adjustable stationary blade of a multistage axial flow compressor cannot adapt to the measurement of all-working-condition airflow parameters, the conventional blade-shaped probe and the blade-shaped probe with an offset angle are effectively combined (namely a combined blade-shaped probe measurement method), wherein the conventional blade-shaped probe is only used for the measurement of a high-rotating-speed area, and the blade-shaped probe with the offset angle is used for the measurement of a medium-low rotating-speed area, so that the complete and accurate measurement of the airflow parameters at the inlet of the adjustable stationary blade of the compressor in a wide working rotating speed variation range is. And by reasonably designing the deflection angle of the blade-shaped probe, the negative influence of the blade-shaped probe with the deflection angle on the internal flow field of the compressor is reduced, the flow field adaptability of the combined blade-shaped probe measurement method is improved, and an effective measurement method is provided for the full-working-condition measurement of the interstage air flow parameters of the multistage axial-flow compressor.
The technical scheme of the invention is as follows: in order to achieve the above object, the technical solution of the present invention is as follows:
a combined blade-type probe measuring method capable of adjusting airflow parameters at a stationary blade inlet is characterized in that at least one blade-type probe is provided with an offset angle when being installed, a direction angle difference theta exists between the blade-type probe and a measuring point of a blade-type probe installed conventionally, the radial position and the number of the measuring points of the blade-type probe with the offset angle are installed, the blade-type probe with the offset angle installed conventionally is the same as the blade-type probe installed conventionally according to requirements, at least one blade-type probe with the offset angle is arranged at the same radial position, the theta is not more than 20 degrees and is not more than the insensitive angle range α ofwThe temperature is not less than 10 ℃, and the conventional blade-shaped probe is used as a high-speed blade-shaped probe and is used for measuring the working condition with the relative conversion rotating speed of more than 90%; the blade-shaped probe with the deflection angle is used as a low-speed blade-shaped probe and is used for measuring the working condition with the relative conversion rotating speed of below 85%.
The leaf-shaped probes are all of a sleeve-shaped structure.
The invention has the beneficial effects that:
the invention provides a combined blade type probe measuring method for measuring adjustable stationary blade inlet airflow parameters, compared with the blade type probe technology in the traditional sense, the combined blade type probe measuring method fully considers the influence of the stationary blade angle adjustment of a multistage axial flow compressor on the blade type probe measurement, and the blade type probe with a deflection angle is adopted to counteract the change of the adjustable stationary blade angle in the compressor at low and medium rotating speed, so that the stationary blade inlet airflow parameters are always in the insensitive angle range of the blade type probe, and the measurement precision of the compressor full-working-condition interstage flow field parameters is obviously improved. Meanwhile, by setting the change range of the deflection angle of the blade-shaped probe, the additional disturbance influence of the blade-shaped probe with the deflection angle on the internal flow field of the compressor is reasonably controlled. The combined blade profile probe measuring method provided by the invention is fully verified in the tests of the blade cascade and the gas compressor, and the verification effect shows that: the combined blade type probe measuring method has a wider insensitive angle measuring range, can remarkably improve the measurement precision of the total pressure parameter of the compressor interstage in a low-and-medium-speed working area, effectively balances the contradiction between the limited insensitive angle range of the conventional blade type probe and the large-angle deflection of the adjustable stationary blade at the low-and-medium speed, and realizes the accurate measurement of the compressor interstage airflow parameter in the whole performance recording rotating speed range.
The method is suitable for the requirement of measuring the parameters of the interstage flow field of the multistage axial flow compressor with the adjustable stationary blade under the whole working condition, is simple and easy to realize, fills the blank of the domestic aviation compressor internal flow test technology, has higher popularization and application values in the field of research of pneumatic performance tests of compression parts of military/civil aviation engines, and is expected to generate good social benefits and economic benefits.
Drawings
FIG. 1 is a schematic view of an improved design of an angularly adjustable stationary blade-type probe according to the present invention;
FIG. 2 is a schematic view of the insensitive angle range of the combined leaf-type probe measurement method of the present invention;
FIG. 3 is a design scheme of a sleeve-type total pressure blade type probe head with an offset angle in the invention.
In FIG. 1, θ is the relative orientation angle of the vane-type probe, β is the inlet geometry angle of the vane, α in FIG. 2wInsensitive angular Width for leaf-type probes, αw+ theta is the insensitive angle range of the combined blade type probe measurement method, and omega is the measurement error. In FIG. 3, θ represents the relative direction angle of the leaf-shaped probe.
The specific implementation mode is as follows:
the present invention will be described in further detail below by way of specific embodiments:
the conventional blade-shaped probe is reserved as a high-speed blade-shaped probe and is used for measuring the parameters of the gas flow between the compressor stages with the relative conversion rotating speed of more than 90 percent, and the blade-shaped probe with the deflection angle is used as a low-speed blade-shaped probe and is used for measuring the parameters of the gas flow between the compressor stages with the relative conversion rotating speed of 85 percent or less, so that the total insensitive angle range of the blade-shaped probe is enlarged, and the blade-shaped probe is enabled to be capable ofThe radial positions and the measuring points of the conventional blade-shaped probe and the blade-shaped probe with the deflection angle are completely the same, namely two blade-shaped probe measuring points with different circumferential positions exist at the same radial position, the larger the relative direction angle theta of the blade-shaped probe measuring point with the deflection angle is, the wider the total insensitive angle range is, and in order to ensure that the total insensitive angle range of the combined blade-shaped probe measuring method is continuous, the relative direction angle theta (shown in figure 2) of the blade-shaped probe measuring point with the deflection angle cannot be larger than αwOtherwise, the combined type leaf-shaped probe measurement method needs to add another group of leaf-shaped probes for transition. The larger the angle of the blade-shaped probe measuring point relative direction is, the more favorable the measurement of the airflow with a large deflection angle at a low rotating speed is, but the blade-shaped probe with the deflection angle can form an airflow deflection angle in the opposite direction at a high rotating speed, and the mach number of the airflow in the compressor at the high rotating speed is larger, so that the pressure measuring pipe trail loss of the blade-shaped probe with the deflection angle is larger, and the extra interference can be brought to the flow field in the compressor at the high rotating speed. In addition, the deflection angle of the measuring point of the leaf-shaped probe is set too large, the processing difficulty of the leaf-shaped probe is increased, and the welding strength is difficult to ensure. Therefore, the relative direction angle of the measuring point of the leaf-shaped probe with the deflection angle is not too large, and is generally not more than 20 degrees. Because the insensitive angle range of the single-tube structure leaf-shaped probe is narrower than that of the sleeve-tube structure leaf-shaped probe, the deflection angle design purpose of the invention can not be achieved by adopting the single-tube structure leaf-shaped probe. Therefore, the blade-shaped probe with the deflection angle is designed to be of a sleeve-shaped structure as the conventional blade-shaped probe.
The following embodiment is a specific application mode of the method under the condition of measuring the airflow parameters of the inlet of the first-stage adjustable stationary blade of the axial flow compressor:
the specific technical scheme for measuring the total pressure of the airflow at the inlet of a certain high-pressure compressor by adopting the combined blade type probe measurement method is expressed as follows:
1) a conventional blade profile probe is reserved as a high-speed blade profile probe and is used for measuring the total pressure of an inlet of a high-pressure compressor with the relative conversion rotating speed of more than 90%, and a blade profile probe with an offset angle is used as a low-speed blade profile probe and is used for measuring the total pressure of the inlet of the high-pressure compressor with the relative conversion rotating speed of 85% or less. In the embodiment, two groups of blades are selected for measurement, each group of two blades is provided with 3 points for one blade, 2 points for one blade are provided for simulating radial 5-point distribution, a radial five-point comb-shaped stable and dynamic total pressure probe is simulated for measuring stable airflow and dynamic total pressure of an inlet of a high-pressure compressor, and the radial positions of the probe are distributed according to equal rings or equal distances. When in measurement, a conventional blade-shaped probe is arranged on one group of blades, a blade-shaped probe with an offset angle is arranged on the other group of blades, the radial positions and the measuring points of the offset-angle blade-shaped probe and the conventional blade-shaped probe are completely the same, namely two blade-shaped probe measuring points with different circumferential positions exist at the same radial position;
2) as shown in FIG. 2, assume that the leaf-type probe has an insensitivity angle in the range of αwWhen the combined blade-type probe measurement method is adopted, the total insensitive angle range is αwThe larger the relative direction angle theta of the measuring point of the blade-shaped probe with the deflection angle is, the wider the total insensitive angle range is, and in order to ensure that the total insensitive angle range of the measuring method of the combined blade-shaped probe continuously changes, the relative direction angle theta of the measuring point of the blade-shaped probe with the deflection angle is not more than αwOtherwise, an additional group of leaf probes is required to be added for transition. The larger the angle of the blade-shaped probe measuring point relative direction is, the more favorable the measurement of the airflow with a large deflection angle at a low rotating speed is, but the blade-shaped probe with the deflection angle can form an airflow deflection angle in the opposite direction at a high rotating speed, and the mach number of the airflow in the compressor at the high rotating speed is larger, so that the pressure measuring pipe trail loss of the blade-shaped probe with the deflection angle is larger, and the extra interference can be brought to the flow field in the compressor at the high rotating speed. In addition, the deflection angle of the measuring point of the leaf-shaped probe is set too large, the processing difficulty of the leaf-shaped probe is increased, and the welding strength is difficult to ensure. Therefore, the relative direction angle of the measuring point of the leaf-shaped probe with the deflection angle is not too large. Therefore, the combined blade profile probe measurement method is adopted to measure the total pressure of the airflow at the inlet of a certain high-pressure compressorWhen the angle is deviated, the relative direction angle of the blade-shaped probe, namely the angle theta in the attached drawing is selected to be 15 degrees;
3) because the insensitive angle range of the single-tube structure leaf-shaped probe is narrower than that of the sleeve-tube structure leaf-shaped probe, the deflection angle design purpose of the invention can not be achieved by adopting the single-tube structure leaf-shaped probe. Therefore, the blade-shaped probe with the deflection angle is the same as the conventional blade-shaped probe, and the sleeve-shaped structural design shown in the attached figure 3 is adopted;
4) the radial positions and the number of the measuring points of the high-speed total pressure blade-shaped probe and the low-speed total pressure blade-shaped probe are completely the same, namely two blade-shaped probe measuring points with different circumferential positions exist at the same radial position, so that the maximum value of the total pressures of the measuring points of the two probes at the same radial position is directly taken as the total pressure at the radial position, and the rotating speed of a test piece does not need to be judged.
Claims (2)
1. A combined blade-type probe measuring method capable of adjusting airflow parameters at a stationary blade inlet is characterized in that at least one blade-type probe is provided with an offset angle when being installed, a direction angle difference theta exists between a measuring point of a conventional blade-type probe without the offset angle and the measuring point, the radial position and the number of the measuring points of the blade-type probe with the offset angle are the same as those of the conventional blade-type probe, at least one blade-type probe with the offset angle is arranged at the same radial position, theta is not more than 20 degrees and is not more than the insensitive angle range α of the blade-type probewAnd not less than 10 degrees, the conventional blade-shaped probe is used as a high-speed blade-shaped probe and is used for measuring the working condition with the relative conversion rotating speed of more than 90 percent; the blade-shaped probe with the deflection angle is used as a low-speed blade-shaped probe and is used for measuring the working condition with the relative conversion rotating speed of below 85%.
2. The method of claim 1, wherein the vane probe is of a thimble-type construction.
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| CN112665861B (en) * | 2021-03-18 | 2021-06-15 | 中国航发上海商用航空发动机制造有限责任公司 | Blade-shaped probe and performance testing method for aircraft engine using same |
| CN115371999B (en) * | 2022-10-24 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Inlet flow field parameter measuring device in high-temperature and high-pressure test |
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| US7527471B2 (en) * | 2006-07-31 | 2009-05-05 | General Electric Company | Stator vane and gas turbine engine assembly including same |
| CN105716779B (en) * | 2015-11-02 | 2019-02-22 | 北京航空航天大学 | Dynamic pressure blade profile probe |
| CN106932139B (en) * | 2017-03-29 | 2020-04-28 | 北京航空航天大学 | Four-hole pressure leaf-shaped probe |
| CN107167283A (en) * | 2017-05-05 | 2017-09-15 | 北京航空航天大学 | A kind of air cooling High Temperature and Stable State pressure probe |
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