CN114961889B - Turbine rotating static disc cavity airflow swirl ratio measuring method - Google Patents
Turbine rotating static disc cavity airflow swirl ratio measuring method Download PDFInfo
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- CN114961889B CN114961889B CN202110193389.6A CN202110193389A CN114961889B CN 114961889 B CN114961889 B CN 114961889B CN 202110193389 A CN202110193389 A CN 202110193389A CN 114961889 B CN114961889 B CN 114961889B
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- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 10
- 238000005259 measurement Methods 0.000 description 9
- 239000000523 sample Substances 0.000 description 6
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 239000000463 material Substances 0.000 description 1
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- 239000010453 quartz Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The invention relates to a turbine rotating static disc cavity airflow swirl ratio measuring method. The measuring method comprises the steps that a first thermocouple is arranged on one side of a static disc, a second thermocouple is arranged on one side of a rotating disc, and the first thermocouple and the second thermocouple are positioned in a cavity of the rotating static disc; total temperature T of the current position air flow obtained according to the first thermocouple * The relative total temperature T obtained by the second thermocouple * w And calculating the airflow rotational flow ratio beta in the rotating and static disc cavity. The invention provides a turbine rotating static disc cavity airflow swirl ratio measuring method which can effectively obtain the airflow swirl ratio in a turbine rotating static disc cavity.
Description
Technical Field
The invention relates to the technical field of aero-engine air system design, in particular to a turbine rotating and static disc cavity airflow swirl ratio measuring method.
Background
The flow field in the flow field of the turbine static disc cavity of the aeroengine is complex, the airflow velocity (mainly in the circumferential direction) in the turbine static disc cavity has a great influence on the heat exchange boundary condition of the turbine disc, and in the flow heat exchange research of the turbine static disc cavity of the aeroengine, domestic and foreign students usually refer to the ratio of the circumferential linear velocity of the airflow at a certain position in the rotating static disc cavity to the circumferential velocity at a corresponding position of the disc wall as a rotational flow ratio. Obviously, the rotational flow ratio of the air flow in the rotating and static disc cavity can be obtained, so that the air flow speed can be reversely pushed, and an important basis is provided for accurate estimation of the heat exchange boundary and the disc temperature field of the turbine disc, design of the reliability of the turbine disc and the like.
In a large state of a real test run of an aero-engine, in order to obtain the flow heat exchange characteristic in the turbine rotating static disc cavity to accurately estimate the temperature field of life-limiting parts such as a turbine disc, the airflow swirl ratio in the turbine rotating static disc cavity needs to be measured. Because the temperature and pressure of the air flow in the turbine static disc cavity are high, the requirements on the temperature resistance and reliability of test equipment are high, the measuring essence of the air flow rotational flow ratio is to measure the circumferential speed of the air flow, and the traditional method for measuring the three-dimensional speed of the air flow mainly comprises a five-hole probe measuring method and a laser measuring method. However, there are many shortcomings and limitations to applying these methods directly to real engine turbine disk cavity swirl ratio measurements, as follows:
1) The five-hole probe method can measure the three-dimensional speed of the air flow, but is limited by the measurement angle of the five-hole probe method, the measurement and calibration related data are complex to process, the test cost is high, the difficulty is high, time and labor are wasted, the error is difficult to reduce, in addition, the five-hole probe material has limited temperature resistance level, and the risk of testing in the high-temperature environment of the actual aeroengine test run is high;
2) The laser measurement method is to determine the three-dimensional speed of the airflow in the disc cavity by using Compton effect and adopting a laser tracking trace particle mode, but the test equipment is complex, a quartz light-transmitting window is usually required to be additionally arranged on the disc or the shaft, and the method is not suitable for measurement in a high-temperature and high-pressure environment of a real engine test.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a turbine rotating static disc cavity airflow rotational flow ratio measuring method which can effectively obtain the airflow rotational flow ratio.
Specifically, the invention provides a turbine rotating static disc cavity airflow swirl ratio measuring method, wherein the turbine comprises a static disc and a rotating disc, a rotating static disc cavity is formed between the static disc and the rotating disc, and the measuring method comprises the following steps:
a first thermocouple is arranged on one side of the static disc, a second thermocouple is arranged on one side of the rotating disc, and the first thermocouple and the second thermocouple are positioned in the rotating static disc cavity;
the total temperature T of the airflow at the current position obtained according to the first thermocouple * And the relative total temperature T obtained by the second thermocouple * w And calculating the airflow rotational flow ratio beta in the rotating and static disc cavity.
According to one embodiment of the invention, the axial distance from the first thermocouple to the second thermocouple is delta X The radial distance from the first thermocouple to the second thermocouple is delta r The axial distance delta X And radial distance delta r Above 0, the first thermocouple and the second thermocouple do not collide during measurement, and the axial distance delta is set X And the radial distance is sufficiently small.
According to one embodiment of the invention, the axial distance Δ X And radial distance delta r Obtained from said thermal deformation of the turbine in axial and radial directions.
According to one embodiment of the invention, the first thermocouple is obtained from the second thermocouple
Total temperature
Relative total temperature
Airflow swirl ratioThereby obtaining the airflow swirl ratio->
Wherein T is static temperature, W 0 For the peripheral speed of the turntable, C p Specific heat, U airflow axial velocity, V airflow radial velocity, W airflow circumferential velocity.
According to one embodiment of the invention, the first thermocouple and/or the second thermocouple are sheathed thermocouples.
According to one embodiment of the invention, the distance from the second thermocouple to the rotating disk is L, and L is more than or equal to 2mm and less than or equal to 4mm.
The method for measuring the airflow swirl ratio of the turbine rotating and static disc cavity provided by the invention can effectively measure and obtain the airflow swirl ratio.
It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as claimed.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. In the accompanying drawings:
fig. 1 shows a schematic structure of a turbine rotor-stator cavity in the prior art.
Fig. 2 shows a schematic structural view of a stationary disc chamber of a turbine wheel according to an embodiment of the present invention.
Fig. 3 shows a flow diagram of a measurement method according to an embodiment of the invention.
Wherein the above figures include the following reference numerals:
stationary plate 101 and rotary plate 102
Rotating shaft 103 rotates static disc cavity 104
First thermocouple 105 second thermocouple 106
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other.
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
In the description of the present application, it should be understood that, where azimuth terms such as "front, rear, upper, lower, left, right", "transverse, vertical, horizontal", and "top, bottom", etc., indicate azimuth or positional relationships generally based on those shown in the drawings, only for convenience of description and simplification of the description, these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present application; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be oriented 90 degrees or at other orientations and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are merely for convenience of distinguishing the corresponding components, and unless otherwise stated, the terms have no special meaning, and thus should not be construed as limiting the scope of the present application. Furthermore, although terms used in the present application are selected from publicly known and commonly used terms, some terms mentioned in the specification of the present application may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Furthermore, it is required that the present application be understood, not simply by the actual terms used but by the meaning of each term lying within.
Fig. 1 shows a schematic structure of a turbine rotor-stator cavity in the prior art, mainly used for explaining the airflow flow form in the turbine rotor-stator cavity. As shown, the turbine includes a stationary disc 101, a rotating disc 102, and a rotating shaft 103. The stationary plate 101 and the rotating plate 102 are arranged in the radial direction of the rotating shaft 103, and a rotating stationary plate chamber 104 is formed between the stationary plate 101 and the rotating plate 102. The air flows along the low radius position of the rotating static disc cavity 104, then flows outwards along the radial direction of the rotating shaft 103, reaches the air outlet gap at the high radius position and then flows out of the rotating static disc cavity 104. In the radial outward flow process, the swirl ratio of the air flow is continuously changed.
Fig. 2 shows a schematic structural view of a turbine stationary disc chamber 104 according to an embodiment of the present invention. As shown, the turbine includes a stationary disc 101, a rotating disc 102, and a rotating shaft 103. The stationary plate 101 and the rotating plate 102 are arranged in the radial direction of the rotating shaft 103, and a rotating stationary plate chamber 104 is formed between the stationary plate 101 and the rotating plate 102. The present invention focuses on arranging a first thermocouple 105 and a second thermocouple 106 on the stationary disc 101 and the rotating disc 102, respectively. The first thermocouple 105 and the second thermocouple 106 are positioned close to each other so that the two can measure the temperature of the same position, and the airflow swirl ratio of the current position is calculated according to the temperatures obtained by the first thermocouple 105 and the second thermocouple 106.
Fig. 3 shows a flow diagram of a measurement method according to an embodiment of the invention. Referring to fig. 2, the invention provides a method for measuring airflow rotational flow ratio of a turbine rotating and static disc cavity 104, which comprises the following steps:
step S1, a first thermocouple 105 is arranged on one side of a static disc 101, a second thermocouple 106 is arranged on one side of a rotating disc 102, and the first thermocouple 105 and the second thermocouple 106 are positioned in a rotating static disc cavity 104;
step S2, obtaining the total temperature T of the airflow at the current position according to the first thermocouple 105 * And the relative total temperature T obtained by the second thermocouple 106 * w The airflow swirl ratio beta in the rotating static disc cavity 104 is calculated.
Preferably, the axial distance from the first thermocouple 105 to the second thermocouple 106 is delta X The radial distance from the first thermocouple 105 to the second thermocouple 106 is delta r Axial distance delta X And radial distance delta r Greater than 0 and at an axial distance delta X And the radial distance is sufficiently small. If the axial distance delta X And radial distance delta r And the space positions of the two are completely consistent when the two are equal to 0, so that the second thermocouple 106 can touch the first thermocouple 105 in a rotating state, displacement occurs, and the measurement result is influenced. Therefore, the distance between the first thermocouple 105 and the second thermocouple 106 is as small as possible on the premise that the first thermocouple and the second thermocouple 106 do not collide during the measurement process, so as to reduceSmall measurement errors.
Preferably, the axial distance delta X And radial distance delta r Obtained from thermal deformations in the axial and radial directions of the turbine.
Preferably, the total temperature T of the current position airflow obtained according to the first thermocouple 105 * And the relative total temperature T obtained by the second thermocouple 106 * w Calculation of
Total temperature
Relative total temperature
Airflow swirl ratioThereby obtaining the airflow swirl ratio->
Wherein T is static temperature, W 0 For the peripheral speed of the turntable, C p Specific heat, U airflow axial velocity, V airflow radial velocity, W airflow circumferential velocity.
Preferably, the first thermocouple 105 and/or the second thermocouple 106 are sheathed thermocouples.
Preferably, the distance from the second thermocouple 106 to the rotating disk 102 is L, where 2 mm.ltoreq.L.ltoreq.4 mm. This arrangement ensures that the test probe of the second thermocouple 106 passes through the thermal boundary layer of the air flow, while avoiding the deviation of the test probe position of the second thermocouple 106 from the target position due to the centrifugal force caused by the high-speed rotation of the rotating disk 102.
Preferably, when the axial width of the rotating disc cavity 104 is larger, in order to measure the temperature at the same position as the second thermocouple 106 on the rotating disc 102 side, the first thermocouple 105 on the rotating disc 101 side can be installed and fixed by designing a mounting seat, so that the whole structure is more stable.
According to the turbine rotating static disc cavity airflow swirl ratio measuring method, thermocouples are respectively arranged on the static disc and the rotating disc, and the temperature resistance degree of the thermocouples is very high, so that the testing precision and reliability are ensured, and the precision of the airflow swirl ratio measured based on the thermocouples can be ensured. Therefore, the method for measuring the airflow swirl ratio of the turbine rotating and static disc cavity can meet the swirl ratio measurement requirement of the turbine rotating and static disc cavity of the real engine in a high-temperature and high-pressure environment.
It will be apparent to those skilled in the art that various modifications and variations can be made to the above-described exemplary embodiments of the present invention without departing from the spirit and scope of the invention. Therefore, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.
Claims (4)
1. A turbine rotor-stator cavity airflow swirl ratio measurement method, the turbine comprising a stator and a rotor, the rotor-stator cavity being formed between the stator and the rotor, the measurement method comprising:
a first thermocouple is arranged on one side of the static disc, a second thermocouple is arranged on one side of the rotating disc, and the first thermocouple and the second thermocouple are positioned in the rotating static disc cavity;
based on the total temperature of the current position air flow obtained by the first thermocoupleAnd the relative total temperature obtained by said second thermocouple +.>Calculating the airflow rotational flow ratio in the rotating static disc cavity>；
The axial distance from the first thermocouple to the second thermocouple is delta X The radial distance from the first thermocouple to the second thermocouple is delta r The axial distance delta X And radial distance delta r Greater than 0, the first during measurementThe thermocouple and the second thermocouple do not collide and the axial distance delta is set X And the radial distance is sufficiently small;
total temperature；
Relative total temperature；
Airflow swirl ratioThereby obtaining the airflow swirl ratio->；
Wherein,for calm temperature, add>For the peripheral speed of the turntable>Specific heat (F)>Axial velocity of air flow->Radial velocity of air flow->The circumferential velocity of the air flow.
2. The measurement method according to claim 1, wherein the axial distance Δ X And radial distance delta r Obtained from said thermal deformation of the turbine in axial and radial directions.
3. The measurement method of claim 1, wherein the first thermocouple and/or the second thermocouple are sheathed thermocouples.
4. The method of measuring of claim 1, wherein the second thermocouple is spaced from the rotating disk by a distance L of 2mm +.l +.4 mm.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2568407A1 (en) * | 2005-11-18 | 2007-05-18 | General Electric Company | Sensor diagnostics using embedded model quality parameters |
| EP2078946A2 (en) * | 2008-01-10 | 2009-07-15 | General Electric Company | Method for operating turbine engines using calculated creep data for the blades |
| WO2010142307A1 (en) * | 2009-06-10 | 2010-12-16 | Universität Stuttgart | Fast response temperature measurement within a gas turbine |
| DE102016102049A1 (en) * | 2016-02-05 | 2017-08-10 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine and method for conditioning the temperature of a turbine disk of a gas turbine |
| CN107605543A (en) * | 2017-08-14 | 2018-01-19 | 西北工业大学 | A kind of dividing disc cavity configuration for wheel rim sealing |
| CN108180077A (en) * | 2016-10-25 | 2018-06-19 | 通用电气公司 | The method that the core-engine speed of gas turbine is limited during icing conditions |
| CN109684767A (en) * | 2019-01-08 | 2019-04-26 | 北京理工大学 | A kind of turbine pump inducer cavitating flows Numerical Predicting Method based on cryogen |
| CN111666648A (en) * | 2019-12-04 | 2020-09-15 | 江西洪都航空工业集团有限责任公司 | Method for simulating dynamic characteristics of aircraft engine |
| CN112098108A (en) * | 2020-08-19 | 2020-12-18 | 西北工业大学 | Gas rotation temperature calibration and verification method on rotating disc |
| CA3122656A1 (en) * | 2020-06-25 | 2021-12-25 | Pratt & Whitney Canada Corp. | System and method for detection of excessive flow in a fluid system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9709448B2 (en) * | 2013-12-18 | 2017-07-18 | Siemens Energy, Inc. | Active measurement of gas flow temperature, including in gas turbine combustors |
| US11305885B2 (en) * | 2019-01-10 | 2022-04-19 | Honeywell International Inc. | Auxiliary power unit adaptive cooldown cycle system and method |
-
2021
- 2021-02-20 CN CN202110193389.6A patent/CN114961889B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2568407A1 (en) * | 2005-11-18 | 2007-05-18 | General Electric Company | Sensor diagnostics using embedded model quality parameters |
| EP2078946A2 (en) * | 2008-01-10 | 2009-07-15 | General Electric Company | Method for operating turbine engines using calculated creep data for the blades |
| WO2010142307A1 (en) * | 2009-06-10 | 2010-12-16 | Universität Stuttgart | Fast response temperature measurement within a gas turbine |
| DE102016102049A1 (en) * | 2016-02-05 | 2017-08-10 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine and method for conditioning the temperature of a turbine disk of a gas turbine |
| CN108180077A (en) * | 2016-10-25 | 2018-06-19 | 通用电气公司 | The method that the core-engine speed of gas turbine is limited during icing conditions |
| CN107605543A (en) * | 2017-08-14 | 2018-01-19 | 西北工业大学 | A kind of dividing disc cavity configuration for wheel rim sealing |
| CN109684767A (en) * | 2019-01-08 | 2019-04-26 | 北京理工大学 | A kind of turbine pump inducer cavitating flows Numerical Predicting Method based on cryogen |
| CN111666648A (en) * | 2019-12-04 | 2020-09-15 | 江西洪都航空工业集团有限责任公司 | Method for simulating dynamic characteristics of aircraft engine |
| CA3122656A1 (en) * | 2020-06-25 | 2021-12-25 | Pratt & Whitney Canada Corp. | System and method for detection of excessive flow in a fluid system |
| CN112098108A (en) * | 2020-08-19 | 2020-12-18 | 西北工业大学 | Gas rotation temperature calibration and verification method on rotating disc |
Non-Patent Citations (2)
| Title |
|---|
| 压气机和涡轮转子三维温度场计算研究;汪好;宋文艳;石德永;;航空工程进展(第03期);第344-350页 * |
| 航空发动机旋转部件流动传热测试方法评述;于霄;吕多;李洪莲;姜楠;赵孟;张筱喆;***;初晴;;计测技术(第S1期);第91-94页 * |
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