CN112963206B - Turbine impeller rotor and stator axial clearance control method - Google Patents
Turbine impeller rotor and stator axial clearance control method Download PDFInfo
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- CN112963206B CN112963206B CN202110134648.8A CN202110134648A CN112963206B CN 112963206 B CN112963206 B CN 112963206B CN 202110134648 A CN202110134648 A CN 202110134648A CN 112963206 B CN112963206 B CN 112963206B
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- turbine
- impeller
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- wheel
- axial clearance
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000004579 marble Substances 0.000 claims description 4
- 238000012545 processing Methods 0.000 claims description 3
- 238000005259 measurement Methods 0.000 abstract description 12
- 238000013461 design Methods 0.000 abstract description 5
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention is suitable for the technical field of centrifugal impeller size conversion, in particular to a turbine impeller stator axial clearance control method, which comprises the following steps: measuring a determined value L5 after the tooling is processed; determining the axial dimensions of the compressor wheel and the turbine wheel; determining an axial clearance L of the turbine wheel and the turbine guide; the measuring tool is tightly attached to the turbine impeller, the highest point of indirect contact between the turbine impeller and the turbine guide is connected in radian, the actual assembly position is simulated, the axial clearance between the curved surface contours of the turbine impeller and the turbine guide is ensured to meet the design requirement, the curved surface contact position is further converted into a plane contact position, and the measuring difficulty is reduced; through measuring the frock, still determined the assembly technical requirement of compressor impeller and turbine impeller's axial position size, whether assembled in place with the axial measurement size judgement between two impellers, improved this kind of engine rotor subassembly axial position's stability, improved production efficiency.
Description
Technical Field
The invention relates to the technical field of centrifugal impeller size conversion, in particular to a turbine impeller stator axial clearance control method.
Background
Aircraft engaged in flight activities, also known as aircraft, are classified as lighter-than-air aircraft and heavier-than-air aircraft. The former relies on aerostatic buoyancy to lift off, such as a balloon, airship, etc., and the latter relies on aerodynamic lift off generated by relative motion with air, such as an aircraft, helicopter, etc. According to whether people are carried or not, the unmanned aerial vehicle can be divided into an unmanned aerial vehicle and an unmanned aerial vehicle.
The aeroengine is a highly complex and precise thermodynamic machine, and is used as the heart of an airplane, not only the power of the airplane in flight, but also an important driving force for promoting the development of aviation industry, and each important change in the human aviation history is indistinguishable from the technical progress of the aeroengine.
Currently, for aeroengines, rotor-stator clearances have a very important impact on the performance and safety of the engine. The clearance is reduced, the fuel consumption rate can be greatly reduced, the flight time is prolonged, and the flight radius can be enlarged. However, if the gap is too small, it may cause rub against each other between the rotors and even serious failure, endangering flight safety.
Therefore, the rotor-stator clearance becomes an important characteristic parameter of the aeroengine. Factors affecting the gap between the rotors and the stators include roundness of the stators, unbalance amount of the rotors, thermal bending of the rotors, and the like in addition to centrifugal deformation and thermal deformation. Therefore, the axial clearance of the rotor and the assembly clearance between the rotors and the stators are required to be strictly controlled during assembly, and the safety and the reliability of the aeroengine are ensured.
Disclosure of Invention
The invention aims to provide a turbine impeller stator axial clearance control method for solving the problems in the background technology. In order to achieve the above purpose, the present invention provides the following technical solutions:
a turbine impeller stator axial clearance control method comprises the following steps:
(1) And measuring a determined value L5 after tooling processing:
11 Firstly, placing a turbine impeller on a turbine guider, enabling the curved surface of the turbine impeller to be in contact with the curve of the guider, and measuring L1;
12 Placing the measuring ring on the turbine guider, placing the turbine impeller, and measuring L2 by contacting the curved surface of the turbine impeller with the position of the measuring ring marked with the dimension;
13 And finally, calculating to obtain the contact size between the wide end face of the measuring tool and the profile of the turbine impeller as L5=L2-L1.
(2) And determining the axial dimensions of the compressor impeller and the turbine impeller, and ensuring that the compressor impeller and the turbine impeller are assembled in place:
21 Placing the measuring tool on the turbine impeller, and measuring the height L3 by using measuring equipment;
22 Placing a compressor impeller with a rotor shaft on the air inlet casing assembly, ensuring contact, and measuring the dimensions L4 and L6 by using equipment;
23 Selecting and adjusting a gasket to adjust the axial distance between the compressor impeller and the turbine impeller: selecting a thickness of "x= (l6+l5) - (l3+l4)", thereby controlling an axial distance between the compressor wheel and the turbine wheel;
(3) Determining the axial clearance L of the turbine wheel from the turbine guide:
31 After the rotor assembly is fixed on the air inlet casing through the oil slinging nut, a measuring tool is placed on the turbine impeller, and then a turbine guider is placed, so that the middle size S is measured;
32 Taking down the measuring tool, fixing the turbine guide by using an actually-working fixing bolt, and measuring the dimension R;
33 Finally, the "R-clearance l=s-L5" is calculated by means of a dimensional chain, resulting in "clearance l=r+c-S", resulting in an axial clearance between the turbine guide and the turbine wheel.
The measuring tool is tightly attached to the turbine impeller, the highest point of indirect contact between the turbine impeller and the turbine guide is connected in radian, the actual assembly position is simulated, the axial clearance between the curved surface contours of the turbine impeller and the turbine guide is ensured to meet the design requirement, the curved surface contact position is further converted into a plane contact position, and the measuring difficulty is reduced; through measuring the frock, still determined the assembly technical requirement of compressor impeller and turbine impeller's axial position size, whether assembled in place with the axial measurement size judgement between two impellers, improved this kind of engine rotor subassembly axial position's stability, improved production efficiency.
The problem of the curved surface size clearance measurement degree of difficulty is big in the assembly process, and measuring result stability is poor is solved.
In the turbine vane rotor axial clearance control method of the invention: the turbine wheel is removably mounted in the rotor assembly.
In the further scheme of the turbine vane wheel stator axial clearance control method, the following steps are provided: the turbine wheel is removably mounted in the turbine guide and removably mounted in the rotor assembly by the turbine guide.
Preferably: the turbine impeller is detachably installed in the turbine guide in a penetrating manner.
In the further scheme of the turbine vane wheel stator axial clearance control method, the following steps are provided: a marble plane is disposed between the turbine wheel and the turbine guide.
In the turbine vane rotor axial clearance control method of the invention: the turbine guide is internally provided with a rotor shaft and a compressor impeller.
In the turbine vane rotor axial clearance control method of the invention: an air inlet casing is assembled outside the turbine guide.
Compared with the prior art, the invention has the beneficial effects that:
the measuring tool is tightly attached to the turbine impeller, the highest point of indirect contact between the turbine impeller and the turbine guide is connected in radian, the actual assembly position is simulated, the axial clearance between the curved surface contours of the turbine impeller and the turbine guide is ensured to meet the design requirement, the curved surface contact position is further converted into a plane contact position, and the measuring difficulty is reduced; through measuring the frock, still determined the assembly technical requirement of compressor impeller and turbine impeller's axial position size, whether assembled in place with the axial measurement size judgement between two impellers, improved this kind of engine rotor subassembly axial position's stability, improved production efficiency.
Drawings
FIG. 1 is a schematic perspective view of a turbine wheel incorporating a rotor assembly of the present invention.
Fig. 2 is a schematic view showing an inverted three-dimensional structure of a turbine wheel according to the present invention.
FIG. 3 is a schematic view of the turbine wheel of FIG. 2 incorporated into a rotor assembly.
FIG. 4 is a schematic cross-sectional view of the turbine wheel of FIG. 1 without the rotor assembly.
Fig. 5 is an enlarged schematic view of the structure of fig. 4 at a.
FIG. 6 is a schematic cross-sectional view of the turbine wheel of FIG. 1 incorporating a rotor assembly.
Fig. 7 is a diagram of the intermediate measurement map of fig. 6.
Fig. 8 is a second intermediate measurement diagram of fig. 6.
Fig. 9 is an enlarged schematic view of the structure at B in fig. 8.
In the figure: 1-a turbine wheel; 2-turbine guide; 3-marble plane; 4-measuring tool.
Detailed Description
The technical scheme of the invention is further described in detail below with reference to the specific embodiments.
In order to stably and reliably solve the problem of axial gap measurement between rotors and stators at the turbine impeller 1 of the aeroengine, the scheme provides the measurement tool 4 matched with the turbine impeller 1, so that the measurement cost is saved, and the stability of the gap is improved; the problem of the curved surface size clearance measurement degree of difficulty is big in the assembly process, and measuring result stability is poor is solved.
In the embodiment of the invention, a turbine impeller rotor stator axial clearance control method comprises the following steps:
(1) The determined value L5 (refer to fig. 2 and 3) after the processing of the measuring tool 4:
11 As shown in fig. 2, the turbine wheel 1 is placed on the turbine guide 2, and the curved surface of the turbine wheel 1 is contacted with the guide curve to measure L1;
12 As shown in fig. 3, placing the measuring ring on the turbine guide 2, putting the turbine impeller 1, and measuring L2 by contacting the curved surface of the turbine impeller 1 with the measuring ring marked with the dimension;
13 And finally, calculating to obtain the contact size between the wide end face of the measuring tool 4 and the profile of the turbine impeller 1, wherein L5=L2-L1.
(2) Determining the axial dimensions of the compressor wheel and the turbine wheel 1, ensuring the assembly in place (see figures 4-6):
21 Placing the measuring tool 4 on the turbine wheel 1, and measuring the height L3 by using measuring equipment;
22 Placing a compressor impeller with a rotor shaft on the air inlet casing assembly, ensuring contact, and measuring the dimensions L4 and L6 by using equipment;
23 Optionally adjusting shims to adjust the axial distance between the compressor wheel and the turbine wheel 1: selecting a thickness of "x= (l6+l5) - (l3+l4)", thereby controlling an axial distance between the compressor wheel and the turbine wheel;
(3) Determining the axial clearance L (see fig. 7-9) of the turbine wheel 1 from the turbine guide 2:
31 After the rotor assembly is fixed on the air inlet casing through the oil slinging nut, a measuring tool 4 is placed on the turbine impeller 1, and then the turbine guider 2 is placed, so that the middle size S is measured;
32 Taking down the measuring tool, fixing the turbine guide 2 by using a fixing bolt which works actually, and measuring the dimension R;
33 Finally, the "R-clearance l=s-L5" is calculated by means of a dimensional chain, resulting in "clearance l=r+c-S", resulting in an axial clearance between the turbine guide 2 and the turbine wheel 1.
The measuring tool 4 is tightly attached to the turbine impeller 1, the highest point of indirect contact between the turbine impeller 1 and the turbine guide 2 is connected in radian, the actual assembly position is simulated, the axial clearance between the curved surface contours of the turbine impeller 1 and the turbine guide 2 is ensured to meet the design requirement, the curved surface contact position is further converted into a plane contact position, and the measuring difficulty is reduced; through measuring frock 4, still determined the assembly technical requirement of the axial position size of compressor impeller and turbine impeller 1, with the axial measurement size judgement between two impellers in place, improved this kind of engine rotor subassembly axial position's stability, improved production efficiency.
In the embodiment of the invention, as shown in fig. 1-9, the turbine wheel 1 is detachably mounted in a rotor assembly; specifically, a marble plane 3 is arranged between the turbine wheel 1 and the turbine guide 2; the turbine wheel 1 is removably mounted in the turbine guide 2 and is removably mounted in the rotor assembly by the turbine guide 2. The turbine wheel 1 is detachably inserted and installed in the turbine guide 2.
A rotor shaft and a compressor impeller are arranged inside the turbine guider 2; in the turbine vane rotor axial clearance control method of the invention: the turbine guide 2 is equipped with an intake casing on the outside.
The working principle of the invention is as follows: the invention discloses a turbine impeller stator axial clearance control method, which comprises the following steps: measuring a determined value L5 after the tooling is processed; determining the axial dimensions of the compressor wheel and the turbine wheel; determining an axial clearance L of the turbine wheel and the turbine guide; the measuring tool is tightly attached to the turbine impeller, the highest point of indirect contact between the turbine impeller and the turbine guide is connected in radian, the actual assembly position is simulated, the axial clearance between the curved surface contours of the turbine impeller and the turbine guide is ensured to meet the design requirement, the curved surface contact position is further converted into a plane contact position, and the measuring difficulty is reduced; through measuring the frock, still determined the assembly technical requirement of compressor impeller and turbine impeller's axial position size, whether assembled in place with the axial measurement size judgement between two impellers, improved this kind of engine rotor subassembly axial position's stability, improved production efficiency.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art in a specific case.
While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (7)
1. The turbine impeller stator axial clearance control method is characterized by comprising the following steps of:
(1) And measuring a determined value L5 after tooling processing:
11 Firstly, placing a turbine impeller on a turbine guider, enabling the curved surface of the turbine impeller to be in contact with the curve of the guider, and measuring L1;
12 Placing the measuring ring on the turbine guider, placing the turbine impeller, and measuring L2 by contacting the curved surface of the turbine impeller with the position of the measuring ring marked with the dimension;
13 Finally, calculating to obtain the contact size between the wide end face of the measuring tool and the profile of the turbine impeller as L5=L2-L1;
(2) And determining the axial dimensions of the compressor impeller and the turbine impeller, and ensuring that the compressor impeller and the turbine impeller are assembled in place:
21 Placing the measuring tool on the turbine impeller, and measuring the height L3 by using measuring equipment;
22 Placing a compressor impeller with a rotor shaft on the air inlet casing assembly, ensuring contact, and measuring the dimensions L4 and L6 by using equipment;
23 Selecting and adjusting a gasket to adjust the axial distance between the compressor impeller and the turbine impeller: selecting a thickness of "x= (l6+l5) - (l3+l4)", thereby controlling an axial distance between the compressor wheel and the turbine wheel;
(3) Determining the axial clearance L of the turbine wheel from the turbine guide:
31 After the rotor assembly is fixed on the air inlet casing through the oil slinging nut, a measuring tool is placed on the turbine impeller, and then a turbine guider is placed, so that the middle size S is measured;
32 Taking down the measuring tool, fixing the turbine guide by using an actually-working fixing bolt, and measuring the dimension R;
33 Finally, the "R-clearance l=s-L5" is calculated by means of a dimensional chain, resulting in "clearance l=r+c-S", resulting in an axial clearance between the turbine guide and the turbine wheel.
2. The turbine wheel rotor-stator axial clearance control method of claim 1 wherein the turbine wheel is removably mounted in a rotor assembly.
3. The turbine wheel rotor-stator axial clearance control method of claim 2 wherein the turbine wheel is removably mounted in the turbine guide and removably mounted in the rotor assembly by the turbine guide.
4. A method of controlling axial clearance of a turbine wheel rotor according to claim 3 in which the turbine wheel is removably mounted in a turbine guide.
5. A turbine wheel stator axial clearance control method in accordance with claim 2 wherein a marble plane is disposed between said turbine wheel and turbine guide.
6. A turbine vane wheel stator axial clearance control method as claimed in any one of claims 1 to 5 wherein the turbine guide is internally provided with a rotor shaft and a compressor wheel.
7. A turbine vane rotor axial clearance control method as claimed in any one of claims 1 to 5 wherein an air inlet casing is fitted to the outside of the turbine guide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110134648.8A CN112963206B (en) | 2021-01-29 | 2021-01-29 | Turbine impeller rotor and stator axial clearance control method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110134648.8A CN112963206B (en) | 2021-01-29 | 2021-01-29 | Turbine impeller rotor and stator axial clearance control method |
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| CN112963206B true CN112963206B (en) | 2024-04-12 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556556A (en) * | 2018-12-18 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of high-pressure turbine in cold conditions assembling process turns stator tip clearance measurement method |
| CN112253264A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7407369B2 (en) * | 2004-12-29 | 2008-08-05 | United Technologies Corporation | Gas turbine engine blade tip clearance apparatus and method |
| US8230726B2 (en) * | 2010-03-31 | 2012-07-31 | General Electric Company | Methods, systems and apparatus relating to tip clearance calculations in turbine engines |
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2021
- 2021-01-29 CN CN202110134648.8A patent/CN112963206B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556556A (en) * | 2018-12-18 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of high-pressure turbine in cold conditions assembling process turns stator tip clearance measurement method |
| CN112253264A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
Non-Patent Citations (1)
| Title |
|---|
| 某型航空发动机低涡静子叶片装配方法研究;牛孝霞;龙洋;;科技风;20200604(第16期);174 * |
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| CN112963206A (en) | 2021-06-15 |
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