CN112963206A - Axial clearance control method for turbine blade wheel stator - Google Patents
Axial clearance control method for turbine blade wheel stator Download PDFInfo
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- CN112963206A CN112963206A CN202110134648.8A CN202110134648A CN112963206A CN 112963206 A CN112963206 A CN 112963206A CN 202110134648 A CN202110134648 A CN 202110134648A CN 112963206 A CN112963206 A CN 112963206A
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- turbine
- impeller
- measuring
- turbine impeller
- axial
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000005259 measurement Methods 0.000 claims abstract description 10
- 239000004579 marble Substances 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram 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
- 230000001737 promoting effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
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- 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
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- 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
Abstract
The invention is suitable for the technical field of size conversion of centrifugal impellers, and particularly relates to a method for controlling axial clearance of a turbine impeller rotor stator, which comprises the following steps: measuring a determined value L5 after the tooling is machined; determining the axial sizes of the compressor impeller and the turbine impeller; determining an axial clearance L between the turbine wheel and the turbine guider; the measuring tool is tightly attached to the turbine impeller, the highest point of indirect contact between the turbine impeller and the turbine guider is connected in a radian, an actual assembly position is simulated, the axial clearance between the turbine impeller and the curved surface profile of the turbine guider 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 the measuring tool, the technical requirements for the assembly of the axial position sizes of the compressor impeller and the turbine impeller are also determined, whether the compressor impeller and the turbine impeller are assembled in place is judged by the axial measurement size between the two impellers, the stability of the axial position of the engine rotor assembly is improved, and the production efficiency is improved.
Description
Technical Field
The invention relates to the technical field of size conversion of centrifugal impellers, in particular to a method for controlling axial clearance of a turbine impeller rotor stator.
Background
Aircraft, also known as aircraft, that engage in flight activities are classified into lighter-than-air aircraft and heavier-than-air aircraft. The former is lifted by air static buoyancy, such as balloons and airships, and the latter is lifted by aerodynamic force generated by relative motion with air, such as airplanes and helicopters. According to whether manned, can be divided into unmanned aerial vehicle and unmanned aerial vehicle.
The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine.
At present, for an aircraft engine, rotor and stator clearances have very important influence on the performance and safety of the engine. The reduction of the clearance can greatly reduce the fuel consumption rate, prolong the flight time and simultaneously enlarge the flight radius. However, if the clearance is too small, rubbing between rotors and stators may result, or even serious failure may occur, compromising flight safety.
Therefore, rotor-stator clearance becomes an important characteristic parameter of an aircraft engine. Factors affecting the gap between the rotors and stators include the roundness of the stators, the unbalance amount of the rotors, the thermal bending of the rotors, and the like, in addition to the centrifugal deformation and the thermal deformation. Therefore, the axial clearance of the rotor and the assembly clearance between the rotor and the stator need to be strictly controlled during assembly, and the safety and the reliability of the aircraft engine are ensured.
Disclosure of Invention
The invention aims to provide a method for controlling axial clearance of a turbine impeller stator, which aims to solve the problems in the background technology. In order to achieve the purpose, the invention provides the following technical scheme:
a method for controlling axial clearance of a turbine impeller stator comprises the following steps:
(1) the determined value L5 after the measurement tool is machined:
11) firstly, placing a turbine impeller on a turbine guider, contacting the curved surface of the turbine impeller with the curve of the guider to measure L1;
12) placing the measuring ring on the turbine guider, then placing a turbine impeller, contacting the curved surface of the turbine impeller with the position of the measuring ring with the size, and measuring to obtain L2;
13) and finally, calculating to obtain the contact size from the wide end face of the measuring tool to the profile of the turbine impeller, wherein the contact size is L5= L2-L1.
(2) Determining the axial sizes of the compressor impeller and the turbine impeller, and ensuring that the assembly is in place:
21) placing the measuring tool on the turbine impeller, and measuring the height L3 by using measuring equipment;
22) placing the compressor impeller with the rotor shaft on the air inlet casing assembly, ensuring contact, and measuring the sizes L4 and L6 by using equipment;
23) and selecting an adjusting gasket to adjust the axial distance between the compressor impeller and the turbine impeller: the matching thickness is 'X = (L6 + L5) - (L3+ L4)', so that the axial distance between the compressor impeller and the turbine impeller is controlled;
(3) determining the axial clearance L between the turbine wheel and the turbine guider:
31) after the rotor assembly is fixed on the air inlet casing through the oil throwing nut, a measuring tool is placed on the turbine impeller, and then a turbine guider is placed on the turbine impeller to measure the middle size S;
32) taking down the measuring tool, fixing the turbine guide by using a fixing bolt which works actually, and measuring the dimension R;
33) finally, the "R-clearance L = S-L5" is calculated by a dimensional chain, giving "clearance L = R + C-S" and the 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 guider is connected in a radian, an actual assembly position is simulated, the axial clearance between the turbine impeller and the curved surface profile of the turbine guider 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 the measuring tool, the technical requirements for the assembly of the axial position sizes of the compressor impeller and the turbine impeller are also determined, whether the compressor impeller and the turbine impeller are assembled in place is judged by the axial measurement size between the two impellers, the stability of the axial position of the engine rotor assembly is improved, and the production efficiency is improved.
The problems of large difficulty in measuring the size clearance of the curved surface and poor stability of a measuring result in the assembling process are solved.
The invention relates to a method for controlling axial clearance of a turbine impeller stator, which comprises the following steps: the turbine wheel is detachably mounted in the rotor assembly.
In a further aspect of the method for controlling axial clearance of a turbine impeller stator of the present invention: the turbine impeller is detachably arranged in the turbine guide device and is detachably arranged in the rotor assembly through the turbine guide device.
Preferably: the turbine impeller is detachably inserted and installed in the turbine guider.
In a further aspect of the method for controlling axial clearance of a turbine impeller stator of the present invention: a marble plane is disposed between the turbine wheel and the turbine guide.
The invention relates to a method for controlling axial clearance of a turbine impeller stator, which comprises the following steps: and a rotor shaft and a compressor impeller are arranged in the turbine guider.
The invention relates to a method for controlling axial clearance of a turbine impeller stator, which comprises the following steps: an air inlet casing is assembled on the outer side of the turbine guider.
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 guider is connected in a radian, an actual assembly position is simulated, the axial clearance between the turbine impeller and the curved surface profile of the turbine guider 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 the measuring tool, the technical requirements for the assembly of the axial position sizes of the compressor impeller and the turbine impeller are also determined, whether the compressor impeller and the turbine impeller are assembled in place is judged by the axial measurement size between the two impellers, the stability of the axial position of the engine rotor assembly is improved, and the production efficiency is improved.
Drawings
Fig. 1 is a schematic view of an upright structure of a turbine wheel mounted in a rotor assembly according to the present invention.
Fig. 2 is a schematic view of an inverted three-dimensional structure of the turbine impeller of the present invention.
Fig. 3 is a schematic view of the turbine wheel of fig. 2 mounted in a rotor assembly.
FIG. 4 is a schematic cross-sectional view of the turbine wheel of FIG. 1 without the rotor assembly installed therein.
Fig. 5 is an enlarged schematic view of a portion a in fig. 4.
Fig. 6 is a schematic cross-sectional view of the turbine wheel of fig. 1 mounted in a rotor assembly.
Fig. 7 is a first clearance measurement diagram of fig. 6.
Fig. 8 is a second view of the gap measurement in 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-a turbine guide; 3-marble plane; and 4, measuring the tool.
Detailed Description
The technical solution of the present invention will be described in further detail with reference to specific embodiments.
In order to stably and reliably solve the problem of measuring the axial clearance between the rotor and the stator at the position of the turbine impeller 1 of the aircraft engine, the scheme provides the measuring tool 4 matched with the turbine impeller 1, so that the measuring cost is saved, and the stability of the clearance is improved; the problems of large difficulty in measuring the size clearance of the curved surface and poor stability of a measuring result in the assembling process are solved.
In the embodiment of the invention, the method for controlling the axial clearance of the turbine impeller stator comprises the following steps:
(1) and a measurement result L5 (see fig. 2 and 3) after the tool 4 is machined:
11) firstly, as shown in fig. 2, a turbine impeller 1 is placed on a turbine guider 2, the curved surface of the turbine impeller 1 is in contact with the curve of the guider, and L1 is measured;
12) as shown in fig. 3, the measuring ring is placed on the turbine guide 2, the turbine wheel 1 is placed, the curved surface of the turbine wheel 1 contacts with the position where the measuring ring is marked with a size, and L2 is measured;
13) and finally, calculating to obtain the contact size from the wide end face of the measuring tool 4 to the molded surface of the turbine impeller 1, wherein the contact size is L5= L2-L1.
(2) Determining the axial dimensions of the compressor impeller and the turbine impeller 1, and ensuring the assembly in place (refer to fig. 4-6):
21) placing the measuring tool 4 on the turbine impeller 1, and measuring the height L3 by using measuring equipment;
22) placing the compressor impeller with the rotor shaft on the air inlet casing assembly, ensuring contact, and measuring the sizes L4 and L6 by using equipment;
23) and selecting an adjusting gasket to adjust the axial distance between the compressor impeller and the turbine impeller 1: the matching thickness is 'X = (L6 + L5) - (L3+ L4)', so that the axial distance between the compressor impeller and the turbine impeller is controlled;
(3) determining the axial clearance L of the turbine wheel 1 and the turbine guide 2 (see fig. 7-9):
31) after the rotor assembly is fixed on the air inlet casing through the oil throwing nut, a measuring tool 4 is placed on the turbine impeller 1, then the turbine guider 2 is placed, and the middle size S is measured;
32) taking down the measuring tool, fixing the turbine guider 2 by using a fixing bolt working actually, and measuring the dimension R;
33) finally, the "R-clearance L = S-L5" is calculated by means of a dimensional chain, the "clearance L = R + C-S" being obtained and the axial clearance between the turbine guide 2 and the turbine wheel 1 being obtained.
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 guider 2 is connected in a radian, an actual assembly position is simulated, the axial clearance between the curved surface profiles of the turbine impeller 1 and the turbine guider 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 confirmed the assembly technical requirement of compressor impeller and turbine wheel 1's axial position size, whether assemble in place is judged with the axial measurement size between two impellers, has improved this kind of engine rotor subassembly axial position's stability, has improved production efficiency.
In the embodiment of the invention, as shown in fig. 1-9, the turbine wheel 1 is detachably mounted in the rotor assembly; specifically, a marble plane 3 is arranged between the turbine impeller 1 and the turbine guider 2; the turbine impeller 1 is detachably installed in the turbine guider 2 and is detachably installed in the rotor assembly through the turbine guider 2. The turbine impeller 1 is detachably inserted and installed in the turbine guider 2.
A rotor shaft and a compressor impeller are arranged in the turbine guider 2; the invention relates to a method for controlling axial clearance of a turbine impeller stator, which comprises the following steps: an air inlet casing is assembled outside the turbine guider 2.
The working principle of the invention is as follows: the invention relates to a method for controlling axial clearance of a turbine impeller rotor stator, which comprises the following steps: measuring a determined value L5 after the tooling is machined; determining the axial sizes of the compressor impeller and the turbine impeller; determining an axial clearance L between the turbine wheel and the turbine guider; the measuring tool is tightly attached to the turbine impeller, the highest point of indirect contact between the turbine impeller and the turbine guider is connected in a radian, an actual assembly position is simulated, the axial clearance between the turbine impeller and the curved surface profile of the turbine guider 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 the measuring tool, the technical requirements for the assembly of the axial position sizes of the compressor impeller and the turbine impeller are also determined, whether the compressor impeller and the turbine impeller are assembled in place is judged by the axial measurement size between the two impellers, the stability of the axial position of the engine rotor assembly is improved, and the production efficiency is improved.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected 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 through specific situations.
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. A method for controlling axial clearance of a turbine impeller stator is characterized by comprising the following steps:
(1) the determined value L5 after the measurement tool is machined:
11) firstly, placing a turbine impeller on a turbine guider, contacting the curved surface of the turbine impeller with the curve of the guider to measure L1;
12) placing the measuring ring on the turbine guider, then placing a turbine impeller, contacting the curved surface of the turbine impeller with the position of the measuring ring with the size, and measuring to obtain L2;
13) and finally, calculating to obtain the contact size from the wide end face of the measuring tool to the profile of the turbine impeller, wherein the contact size is L5= L2-L1.
(2) Determining the axial sizes of the compressor impeller and the turbine impeller, and ensuring that the assembly is in place:
21) placing the measuring tool on the turbine impeller, and measuring the height L3 by using measuring equipment;
22) placing the compressor impeller with the rotor shaft on the air inlet casing assembly, ensuring contact, and measuring the sizes L4 and L6 by using equipment;
23) and selecting an adjusting gasket to adjust the axial distance between the compressor impeller and the turbine impeller: the matching thickness is 'X = (L6 + L5) - (L3+ L4)', so that the axial distance between the compressor impeller and the turbine impeller is controlled;
(3) determining the axial clearance L between the turbine wheel and the turbine guider:
31) after the rotor assembly is fixed on the air inlet casing through the oil throwing nut, a measuring tool is placed on the turbine impeller, and then a turbine guider is placed on the turbine impeller to measure the middle size S;
32) taking down the measuring tool, fixing the turbine guide by using a fixing bolt which works actually, and measuring the dimension R;
33) finally, the "R-clearance L = S-L5" is calculated by a dimensional chain, giving "clearance L = R + C-S" and the axial clearance between the turbine guide and the turbine wheel.
2. The method as claimed in claim 1, wherein the turbine impeller is detachably mounted in the rotor assembly.
3. The method as claimed in claim 2, wherein the turbine wheel is detachably mounted in the turbine guide and is detachably mounted in the rotor assembly via the turbine guide.
4. The method as claimed in claim 3, wherein the turbine wheel is removably inserted into the turbine guide.
5. The method as claimed in claim 2, wherein marble planes are disposed between the turbine impeller and the turbine vane.
6. The method as claimed in any one of claims 1 to 5, wherein the turbine guide is provided with a rotor shaft and a compressor wheel inside.
7. The method for controlling the axial clearance of the turbine rotor and stator according to any one of claims 1 to 5, wherein an air inlet casing is assembled outside 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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
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| CN112963206A true CN112963206A (en) | 2021-06-15 |
| CN112963206B CN112963206B (en) | 2024-04-12 |
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| CN202110134648.8A Active CN112963206B (en) | 2021-01-29 | 2021-01-29 | Turbine impeller rotor and stator axial clearance control method |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060140756A1 (en) * | 2004-12-29 | 2006-06-29 | United Technologies Corporation | Gas turbine engine blade tip clearance apparatus and method |
| US20110243708A1 (en) * | 2010-03-31 | 2011-10-06 | General Electric Company | Methods, systems and apparatus relating to tip clearance calculations in turbine engines |
| 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 |
-
2021
- 2021-01-29 CN CN202110134648.8A patent/CN112963206B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060140756A1 (en) * | 2004-12-29 | 2006-06-29 | United Technologies Corporation | Gas turbine engine blade tip clearance apparatus and method |
| US20110243708A1 (en) * | 2010-03-31 | 2011-10-06 | General Electric Company | Methods, systems and apparatus relating to tip clearance calculations in turbine engines |
| 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 |
|---|
| 牛孝霞;龙洋;: "某型航空发动机低涡静子叶片装配方法研究", 科技风, no. 16, 4 June 2020 (2020-06-04), pages 174 * |
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| CN112963206B (en) | 2024-04-12 |
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