CN112665861B - Blade-shaped probe and performance testing method for aircraft engine using same - Google Patents
Blade-shaped probe and performance testing method for aircraft engine using same Download PDFInfo
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- CN112665861B CN112665861B CN202110288773.4A CN202110288773A CN112665861B CN 112665861 B CN112665861 B CN 112665861B CN 202110288773 A CN202110288773 A CN 202110288773A CN 112665861 B CN112665861 B CN 112665861B
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Abstract
The invention provides a blade-shaped probe and a method for testing the performance of an aeroengine by using the same. The leaf-shaped probe comprises: stator vanes as struts; a stagnation cover fixed on the front edge of the stator blade and internally provided with a measuring device; and the stator blade is divided into a front section blade and a rear section blade along the chord direction, the stagnation cover is fixed on the front edge of the front section blade, the front section blade is provided with a rotating shaft, and the front section blade can rotate along with the rotating shaft.
Description
Technical Field
The invention relates to a blade-shaped probe, in particular to a blade-shaped probe for detailed measurement of an internal flow field between mechanical stages of an engine impeller, and an aircraft engine performance testing method using the blade-shaped probe.
Background
With the development of science and technology, the requirements of modern aircraft engines on economy and reliability are higher and higher, and the performance of each component of the aircraft engine meets unprecedented challenges.
Due to the limitations of computational software analysis, performance testing is an indispensable process for aircraft engine development. Experience at home and abroad shows that the design verification, optimization improvement and the like of a successful aero-engine can not be separated from reliable performance test and accurate pneumatic parameter measurement.
The blade-type probe is one of devices widely used for measuring the internal flow field between mechanical stages of an aircraft engine impeller in detail at present. The original stator blade of the impeller machinery is taken as a supporting rod, and a plurality of measuring devices for total temperature, total pressure and the like are radially arranged on the front edge of the stator blade and used for measuring the pressure, temperature value and distribution of the outlet of a rotor, so that the detail flow field between stages of the impeller machinery is obtained. Compared with the traditional support rod type measuring probe, the blade type measuring probe can greatly reduce the blockage and interference of the measuring probe to the air flow channel, and can reduce the negative influence of the measuring probe on the mechanical performance of the impeller in the test process, thereby obtaining more real pneumatic performance.
Patent document 1 discloses a four-hole pressure vane probe which is distributed along the height of a blade, can simultaneously measure the total pressure, static pressure, airflow angle and mach number of incoming flow at a plurality of spatial positions, and is suitable for measuring the distribution of incoming flow parameters of an interstage three-dimensional flow field of an aircraft engine along the height direction of the blade.
Patent document 2 discloses a dynamic pressure probe in which a small dynamic pressure sensor is mounted in a stagnation cover, and the stagnation cover is fixed near the leading edge of a blade, thereby forming a contact measurement.
Patent document 3 discloses a probe adjustment method. Wherein the machine is equipped with a rotatably adjustable probe inserted in the gap between adjacent rows or stages of turbine blades for measuring the characteristic flow angle of the compressible working medium flowing through the machine, which measurement is transmitted to an adjuster which functions to adjust the rotational position of the turbine blades, i.e. the blade angle, when the flow angle of the medium deviates from a predetermined value.
Documents of the prior art
Patent document
Patent document 1: CN 106932139A;
patent document 2: CN 105716779A;
patent document 3: US 3327933A.
Disclosure of Invention
The technical problems to be solved by the invention are as follows:
under ideal conditions, the airflow angle is relatively parallel to the inlet airflow angle in the designed state, and the airflow parameters can be measured more accurately. However, in a non-ideal state (a non-design state), the airflow inlet angle of the front edge of the stator blade changes and forms a certain included angle with the stagnation cover. As a result, when the axial included angle between the airflow and the stagnation cover is not in the insensitive angle range, the blade-type probe cannot accurately measure the airflow parameters.
In patent documents 1 to 3, the mounting angles of the stagnation covers mounted on the leading edge of the blade in the chord direction of the blade are all fixed. However, the aeroengine impeller machinery has quite complex operation conditions, complex internal flow field and large angle change when the airflow operates under a plurality of different conditions. In the actual operation process of the impeller machine, the air flow angle change under different working conditions and different operation states often exceeds the insensitive angle range. When the incident angle of the airflow exceeds the insensitive angle range of the blade-shaped probe, the testing precision of the airflow is greatly reduced, and the accuracy of flow field measurement cannot be met, so that the performance verification of the aero-engine is seriously influenced.
The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a vane-type probe and a method for testing the performance of an aircraft engine using the vane-type probe, in which a rotation shaft is provided to a front blade of the vane-type probe to enable the front blade to rotate with the rotation shaft, so that an angle formed by a stagnation cover fixed to the front blade and an intake airflow in an axial direction of the rotation shaft can be finally within an insensitive angle range of the stagnation cover, thereby improving the measurement accuracy of the vane-type probe in a plurality of operating conditions of an impeller machine.
The technical scheme for solving the technical problem is as follows:
a leaf probe according to an embodiment of the present invention includes: stator vanes as struts; a stagnation cover fixed on the front edge of the stator blade and internally provided with a measuring device; the vane-type probe is characterized in that the stator vane is divided into a front section vane and a rear section vane along the chord direction, the stagnation cover is fixed on the front edge of the front section vane, the front section vane is provided with a rotating shaft, and the front section vane can rotate along with the rotating shaft.
In the leaf-shaped probe according to the second aspect of the present invention according to the first aspect, it is preferable that the fixing portion includes: the upper circular truncated cone and the lower circular truncated cone are used for fixing the front-section blade; and an upper end fixing part and a lower end fixing part for fixing the rear blade.
In the blade-type probe according to the third aspect of the present invention, in the second aspect, it is preferable that the upper circular truncated cone is attached to an outer casing, the lower circular truncated cone is attached to an inner casing, the front blade is fixed by the upper circular truncated cone and the lower circular truncated cone, and the upper circular truncated cone, the lower circular truncated cone, the rotation shaft, and the front blade are integrally configured so that the upper circular truncated cone, the lower circular truncated cone, and the front blade are driven to rotate together around the same center line when the rotation shaft rotates.
In the leaf-type probe according to the fourth aspect of the present invention, in any one of the first to third aspects, it is preferable that the rotation shaft rotates clockwise or counterclockwise.
In the blade-type probe according to the fifth aspect of the present invention, in the second aspect, it is preferable that the upper end fixing portion is attached to an outer casing, the lower end fixing portion is attached to an inner casing, the rear blade is fixed by the upper end fixing portion and the lower end fixing portion, and the upper end fixing portion, the lower end fixing portion, and the rear blade are integrally formed.
In the leaf probe according to a sixth aspect of the present invention, in the first aspect, it is preferable that the measurement device includes a total pressure sensor and a total temperature sensor.
In the vane-type probe according to the seventh aspect of the present invention, in the first aspect, it is preferable that the stagnation cover is fixed to the stator vane by bonding or welding.
In an aircraft engine performance testing method according to an embodiment of the present invention, a performance test is performed using the vane-type probe according to any one of the first to seventh aspects, wherein the leading blade is rotated such that an angle formed by a stagnation cover fixed to the leading blade and an intake airflow in an axial direction of a rotation shaft is within an insensitive angle range of the stagnation cover.
In the aircraft engine performance testing method according to the ninth aspect of the present invention, in the eighth aspect, it is preferable that the stagnation cover fixed to the front-stage blade and the intake airflow face each other in the rotation axis axial direction.
In the aircraft engine performance testing method according to the tenth aspect of the present invention according to the eighth or ninth aspect, the insensitive angle range of the stagnation cover is preferably ± 15 ° to ± 20 °.
The invention has the following effects:
according to the blade-shaped probe and the aircraft engine performance testing method using the blade-shaped probe, the rotating shaft is arranged on the front blade of the blade-shaped probe, so that the front blade can rotate along with the rotating shaft, the angle formed by the stagnation cover fixed on the front blade and the air inlet flow in the axial direction of the rotating shaft is finally in the insensitive angle range of the stagnation cover, and therefore the measuring accuracy of the blade-shaped probe under multiple operating conditions of the impeller machinery can be improved.
Drawings
FIG. 1 is a diagram showing the overall configuration of a leaf-type probe according to an embodiment of the present invention.
Fig. 2 is a schematic view showing the rotation of the leaf-type probe according to the embodiment of the present invention.
Fig. 3 is a diagram illustrating an insensitive angle range of the stagnation cover.
Fig. 4 is a schematic view showing an angle formed by the stagnation cover and the intake airflow in the axial direction of the rotation axis.
FIG. 5 is a schematic diagram illustrating the rotation of the forward stage blades and the stagnation cover.
Number designation in the figures: a 100-leaf probe; 11 a front section blade; 12 rear blade; 13 an upper circular truncated cone; 14 a lower circular truncated cone; 15 a stagnation cover; 16 upper end fixing part; 17 a lower end fixing part; 18 test lines; 19 a rotating shaft; the insensitive angle range of the beta stagnation cover; the angle formed by the theta intake airflow and the stagnation cover in the axial direction of the rotating shaft; alpha inlet airflow angle.
Detailed Description
Hereinafter, specific embodiments of the present invention will be described with reference to the drawings.
Fig. 1 is a diagram showing an overall configuration of a leaf probe 100 according to an embodiment of the present invention.
As shown in fig. 1, the blade-type probe 100 includes a front blade 11, a rear blade 12, a stagnation cover 15, an upper circular truncated cone 13, a lower circular truncated cone 14, an upper end fixing portion 16, a lower end fixing portion 17, and a rotating shaft 19.
The front blade 11 and the rear blade 12 constitute stator blades. The stator blade is obtained by a general aerodynamic design flow of an axial compressor (not shown), and functions as a strut. The general pneumatic design process comprises one-dimensional design, through-flow design, blade profile design, three-dimensional calculation analysis and the like.
The stator blade is segmented into a front blade 11 and a rear blade 12 in the chord direction as shown in fig. 1.
A stagnation cover 15, in which a measuring device (not shown) such as a total pressure sensor or a total temperature sensor is installed, is attached to the front edge of the front blade 11. The stagnation cover 15 is connected to the front blade 11 by welding, bonding, or the like.
The front blade 11 is fixed by an upper circular truncated cone 13 and a lower circular truncated cone 14, and the front blade 11 is provided with a rotating shaft 19. The upper circular table 13, the front blade 11, the lower circular table 14, and the rotating shaft 19 are integrally formed.
That is, the front blade 11 can rotate clockwise or counterclockwise with respect to the rotation shaft 19. At this time, when the rotary shaft 19 is rotated by the external adjustment mechanism (not shown), the upper circular table 13 and the lower circular table 14, which are integrally formed with the front blade 11, are also rotated clockwise or counterclockwise around the same center line, i.e., the test line 18 in fig. 1. The upper circular table 13 is attached to the outer casing, and the lower circular table 14 is attached to the inner casing, thereby fixing the front blade 11.
The rear blade 12 segmented in the chord direction is fixed by an upper end fixing portion 16 and a lower end fixing portion 17. Specifically, the rear blade 12, the upper end fixing portion 16, and the lower end fixing portion 17 are integrally formed, the upper end fixing portion 16 is attached to the outer casing, and the lower end fixing portion 17 is attached to the inner casing, thereby fixing the rear blade 12.
The rear blades 12 are separated from the front blades 11, and the rear blades 12 do not rotate but remain stationary.
Fig. 2 is a schematic view showing the rotation of the leaf-type probe 100 according to the embodiment of the present invention.
Specifically, the rotary shaft 19 is rotated when driven by an external adjustment mechanism (not shown), and simultaneously rotates the upper circular table 13, the front blade 11, and the lower circular table 14, which are integrally formed. As shown in the upper part of fig. 2, the front blade 11 may rotate clockwise or counterclockwise by the rotation shaft 19.
The line a-a in fig. 2 indicates the planar direction of the front blade 11 perpendicular to the rotation axis 19, and the line B-B in fig. 2 indicates the planar direction of the rear blade 12 perpendicular to the rotation axis 19. Because the rear blade 12 is always still and does not rotate, when the front blade 11 rotates, the front blade 11 and the rear blade 12 are not located on the same plane, and a rotation included angle exists between the line A-A and the line B-B. The rotation amount (rotation angle) of the front blade 11 can be clearly understood by the rotation angle.
Next, the insensitive angle range of the stagnation cover 15 will be described with reference to fig. 3 and 4.
Specifically, fig. 3 and 4 are sectional views taken along line a-a in fig. 2. As shown in fig. 3 and 4, the stagnation cover 15 is fixed to the front edge of the front blade 11 by welding, bonding, or the like. The front blade 11 faces the intake direction of the airflow 20 (i.e., the inlet of the intake airflow 20), and the airflow 20 passes through the stator blades (the front blade 11 and the rear blade 12) of the vane-type probe 100, so that the rear blade 12 is the outlet of the intake airflow 20.
Since the front blade 11 rotates about the rotation shaft 19, the stagnation cover 15 also rotates together with the front blade 11. In fig. 3 and fig. 4 to 5 described later, the axial direction of the rotary shaft 19 is indicated by a broken line.
As shown in fig. 4, when the intake airflow 20 is blown toward the front-stage blades 11, an angle formed between the intake airflow 20 and the stagnation cover 15 in the axial direction of the rotation shaft 19 is θ.
Typically, the stagnation housing 15 disposed at the leading edge of the vane-type probe 100 has a certain insensitive angular range. When the angle theta formed by the intake airflow 20 and the stagnation cover 15 in the axial direction of the rotating shaft 19 is within the insensitive angle range, the vane-type probe 100 can measure the airflow parameters more accurately.
On the contrary, when the angle θ formed by the intake airflow 20 and the stagnation cover 15 in the axial direction of the rotating shaft 19 is not within the insensitive angle range, that is, when the incident angle of the intake airflow 20 exceeds the insensitive angle range of the stagnation cover 15, the test precision is greatly reduced, and the accuracy of the flow field measurement cannot be met, so that the performance verification of the aircraft engine is seriously affected.
The insensitive angle range of the stagnation cover 15 is normally ± 15 ° to ± 20 °, as indicated by an angle β in fig. 3.
That is, in the actual performance test, in general, when the angle θ formed by the intake airflow 20 shown in fig. 4 and the stagnation cover 15 in the axial direction of the rotation shaft 19 is always within the insensitive angle range β shown in fig. 3, the vane-type probe 100 can measure the airflow parameter more accurately.
In addition, in order to further improve the accuracy of the airflow field measurement, it is preferable to face the stagnation cover 15 to the intake airflow 20. That is, it is preferable that the angle θ between the intake airflow 20 shown in fig. 4 and the stagnation cover 15 in the axial direction of the rotation shaft 19 be 0 °. In this case, the test effect is optimal.
Next, the rotation of the front blade 11 when the direction of the intake airflow 20 changes will be described. Fig. 5 is a schematic view showing the rotation of the front blade 11 and the stagnation cover 15.
To better describe the rotation of the front blade 11 and the stagnation cover 15, the inlet airflow angle, i.e., the angle of the intake airflow 20 with respect to the horizontal direction of the paper surface in fig. 5 is denoted as α.
As shown in fig. 5 (a), in the initial state, the intake airflow 20 is opposed to the stagnation cover 15, and θ is 0 °. That is, in this case, the angle θ formed between the intake airflow 20 and the stagnation cover 15 in the axial direction of the rotation shaft 19 is within the insensitive angle range β of the stagnation cover 15. In addition, the inlet airflow angle at this time is denoted as α1。
As shown in fig. 5 (B), when the direction of the intake airflow 20 changes, that is, the inlet airflow angle becomes α2(case of decrease, α)2＜α1) At this time, the front stage blades 11 are rotated accordingly so that the intake airflow 20 is kept opposed to the stagnation cover 15 even if the angle θ formed between the intake airflow 20 and the stagnation cover 15 in the axial direction of the rotation shaft 19 is kept at 0 °. In this case, as shown in fig. 5 (B), the front blade 11 may be rotated clockwise.
As shown in fig. 5 (C), when the direction of the intake airflow 20 changes, that is, the inlet airflow angle becomes α3(case of increasing, α)3＞α1) At this time, the front stage blades 11 are rotated accordingly so that the intake airflow 20 is kept opposed to the stagnation cover 15 even if the angle θ formed between the intake airflow 20 and the stagnation cover 15 in the axial direction of the rotation shaft 19 is kept at 0 °. In this case, as shown in fig. 5 (C), the front blade 11 may be rotated counterclockwise.
As described above, according to the vane-type probe of the present invention, the stator blade of the vane-type probe is segmented into the front blade and the rear blade along the chord direction, and the rotation shaft is provided to the front blade to enable the front blade to rotate along with the rotation shaft, so that the angle formed by the stagnation cover fixed to the front blade and the intake airflow in the axial direction of the rotation shaft can be finally within the insensitive angle range of the stagnation cover, thereby improving the measurement accuracy of the vane-type probe under a plurality of operating conditions of the vane machine.
In the above embodiment, the manner of adjusting the front-stage blades in the case where the inlet airflow angle changes when the intake airflow faces the stagnation cover has been described. However, even when the intake airflow and the stagnation cover do not completely face each other, the same effect can be achieved as long as the rotation of the front-stage blades can be adjusted so that the angle formed by the stagnation cover fixed to the front-stage blades and the intake airflow in the axial direction of the rotation shaft is within the insensitive angle range of the stagnation cover.
Although the exemplary embodiments have been described in the present application, the features, forms, and functions described in the embodiments are not limited to the specific embodiments, and may be applied to the embodiments individually or in various combinations.
Therefore, numerous modifications not illustrated are also contemplated as falling within the technical scope disclosed in the present application. For example, the case where at least 1 component is modified, added, or omitted is also included.
Industrial applicability of the invention
The blade-shaped probe provided by the invention is simple in structure and easy to realize, can greatly improve the adaptability and the measurement accuracy of the blade-shaped probe under all working conditions in the test of the aeroengine, and has higher popularization and application values in the field of aeroengine pneumatic parameter measurement.
Claims (10)
1. A leaf-type probe comprising: stator vanes as struts; a stagnation cover fixed on the front edge of the stator blade and internally provided with a measuring device; and a fixing portion for fixing the stator blade, characterized in that,
the stator blade is segmented into a front blade and a rear blade along the chord direction,
fixing the stagnation cover to the front edge of the front section blade,
the front section blades are provided with rotating shafts, and the front section blades can rotate along with the rotating shafts.
2. The leaf-type probe of claim 1,
the fixing portion includes:
the upper circular truncated cone and the lower circular truncated cone are used for fixing the front-section blade; and
and the upper end fixing part and the lower end fixing part are used for fixing the rear section blade.
3. The leaf-type probe of claim 2,
the upper circular truncated cone is arranged on the outer casing, the lower circular truncated cone is arranged on the inner casing, the front-section blade is fixed through the upper circular truncated cone and the lower circular truncated cone,
the upper circular truncated cone, the lower circular truncated cone, the rotating shaft, and the front blade are formed integrally,
when the rotating shaft rotates, the upper circular table, the lower circular table and the front-section blade are driven to rotate around the same central line.
4. The leaf-type probe of any one of claims 1 to 3,
the rotation shaft performs clockwise rotation or counterclockwise rotation.
5. The leaf-type probe of claim 2,
the upper end fixing part is arranged on the outer casing, the lower end fixing part is arranged on the inner casing, the rear-section blade is fixed through the upper end fixing part and the lower end fixing part,
the upper end fixing portion, the lower end fixing portion, and the rear blade are integrally formed.
6. The leaf-type probe of claim 1,
the measuring device comprises a total pressure sensor and a total temperature sensor.
7. The leaf-type probe of claim 1,
the stagnation cover is fixed on the stator blade through bonding and welding.
8. An aircraft engine performance testing method using the vane-type probe according to any one of claims 1 to 7 for performance testing,
and rotating the front section blades so that the angle formed by the stagnation cover fixed on the front section blades and the inlet airflow in the axial direction of the rotating shaft is in the insensitive angle range of the stagnation cover.
9. The aircraft engine performance testing method of claim 8,
the stagnation cover fixed to the front blade is opposed to the intake airflow in the axial direction of the rotary shaft.
10. The aircraft engine performance testing method according to claim 8 or 9,
the insensitive angle range of the stagnation cover is +/-15 degrees to +/-20 degrees.
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| CN202110288773.4A CN112665861B (en) | 2021-03-18 | 2021-03-18 | Blade-shaped probe and performance testing method for aircraft engine using same |
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| CN202110288773.4A CN112665861B (en) | 2021-03-18 | 2021-03-18 | Blade-shaped probe and performance testing method for aircraft engine using same |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US11719165B2 (en) | 2021-11-03 | 2023-08-08 | Pratt & Whitney Canada Corp. | Air inlet strut for aircraft engine |
| US11859561B2 (en) | 2021-12-07 | 2024-01-02 | Pratt & Whitney Canada Corp. | Method and system for determining aircraft engine inlet total pressure |
| US11840346B2 (en) | 2022-03-28 | 2023-12-12 | Pratt & Whitney Canada Corp. | Strut for aircraft engine |
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| US4050306A (en) * | 1976-02-27 | 1977-09-27 | General Electric Company | Method and apparatus for measuring pressures |
| JP3631889B2 (en) * | 1997-09-10 | 2005-03-23 | 三菱重工業株式会社 | Contact-type clearance measuring device |
| KR100367555B1 (en) * | 2000-11-16 | 2003-01-10 | 한국항공우주산업 주식회사 | Integration type sensor for wind tunnel test of aircraft |
| US8925387B2 (en) * | 2012-12-19 | 2015-01-06 | United Technologies Corporation | Traversing time of arrival probe |
| CN105715585B (en) * | 2014-12-05 | 2019-06-28 | 上海电气集团股份有限公司 | Variable-geometry exit guide blade |
| CN104595245B (en) * | 2015-01-04 | 2016-12-07 | 南京航空航天大学 | The adjustable stator blade of first half section and method of work thereof for axial flow compressor final stage |
| CN105716779B (en) * | 2015-11-02 | 2019-02-22 | 北京航空航天大学 | Dynamic pressure blade profile probe |
| CN205192393U (en) * | 2015-11-17 | 2016-04-27 | 沈阳黎明航空发动机(集团)有限责任公司 | Switching joint of adjustable three -dimensional probe angle |
| CN206054385U (en) * | 2016-08-10 | 2017-03-29 | 上海电气燃气轮机有限公司 | Improve the sectional-regulated exit guide blade and its governor motion of compressor off design performance |
| CN106918410B (en) * | 2017-03-29 | 2020-11-17 | 北京航空航天大学 | Total temperature leaf type probe |
| CN109372788B (en) * | 2018-12-10 | 2020-09-25 | 中国航发四川燃气涡轮研究院 | Combined blade type probe measuring method capable of adjusting airflow parameters of stationary blade inlet |
| CN209724784U (en) * | 2019-04-10 | 2019-12-03 | 中国航发商用航空发动机有限责任公司 | Gas-turbine unit, fan and split type adjustable stator blade |
| CN111337261B (en) * | 2020-01-10 | 2021-11-30 | 西北工业大学 | Rotary machine interstage and outlet total pressure probe |
| CN111413004B (en) * | 2020-03-31 | 2021-11-12 | 中国航发湖南动力机械研究所 | Temperature probe and method for measuring temperature of air flow |
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