CN113199237B - Method for assembling low-pressure turbine guider of aircraft engine and coaxiality auxiliary control device - Google Patents
Method for assembling low-pressure turbine guider of aircraft engine and coaxiality auxiliary control device Download PDFInfo
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- CN113199237B CN113199237B CN202110430012.8A CN202110430012A CN113199237B CN 113199237 B CN113199237 B CN 113199237B CN 202110430012 A CN202110430012 A CN 202110430012A CN 113199237 B CN113199237 B CN 113199237B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/10—Aligning parts to be fitted together
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/003—Measuring of motor parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
- G01B5/25—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses an aircraft engine low-pressure turbine guider assembling method and a coaxiality auxiliary control device. According to the invention, the auxiliary control device is assembled on the rear mounting edge of the low-pressure turbine guider, the coaxiality is checked by utilizing the inner ring surface in the auxiliary control device, the jumping value of the inner ring surface is detected by matching with a dial indicator or a dial indicator, then the tightness degree of bolts of the low-pressure turbine guider and the rear mounting edge of the combustion chamber casing is adjusted, the jumping value of the inner ring surface is controlled by a cross method, and finally the low-pressure turbine guider meets the requirement of assembling coaxiality.
Description
Technical Field
The invention belongs to the technical field of aircraft engine complete machine assembly test runs, and particularly relates to a coaxiality control device and an assembly method in the assembly process of a low-pressure turbine guider.
Background
The control of the assembly coaxiality of the aero-engine casing is the key point for ensuring the working performance and the operation safety of the engine. The assembly coaxiality of the low-pressure turbine guider case takes the fitting circular run-out of the precise mounting hole of the engine axis reference detection case as a reference, and the coaxiality is adjusted through the tightening degree of the connecting bolt of the joint surface, wherein the requirement is less than or equal to 0.05 mm.
At present, whether the assembly coaxiality of the low-pressure turbine guider meets the requirement or not is difficult to judge due to the fact that a precise mounting hole fitting circle and circle jumping detection means are not available temporarily.
Disclosure of Invention
The invention aims to provide an assembling method of a low-pressure turbine guider of an aircraft engine and a coaxiality auxiliary control device, which can be used for assisting in controlling the assembling coaxiality of the low-pressure turbine guider of the engine, realizing the detection of the coaxiality in the assembling process and providing an assembling guidance function.
In order to achieve the purpose, the invention adopts the following technical scheme:
an auxiliary control device for the coaxiality of the guide device assembly of a low-pressure turbine of an aircraft engine comprises,
the auxiliary device comprises an auxiliary device main body, a positioning device and a positioning device, wherein the auxiliary device main body is a circular ring, and the auxiliary device main body is provided with an inner ring surface coaxial with the auxiliary device main body, and a plurality of first precise positioning holes, first connecting holes and second connecting holes parallel to the axial direction of the auxiliary device main body;
the precise positioning pin is inserted into a first precise positioning hole in the auxiliary device main body and a second precise positioning hole in the rear mounting edge of the low-pressure turbine guider; the second precision positioning hole is positioned on the rear mounting edge of the low-pressure turbine guider, the second precision positioning hole is matched with the first precision positioning hole in position and quantity, the second precision positioning hole on the rear mounting edge of the low-pressure turbine guider is used for ensuring the mounting concentricity with the turbine support in the subsequent process, and meanwhile, the corresponding second precision positioning hole is designed according to the reference in order to better reflect the assembly concentricity of the low-pressure turbine guider;
a connection bolt connected with a first connection hole on the auxiliary device main body;
and the lifting ring is connected with a second connecting hole in the auxiliary device main body.
The method for assembling the low-pressure turbine guider of the aircraft engine by adopting the low-pressure turbine guider assembly coaxiality auxiliary control device comprises the following steps,
connecting the front mounting edge of the low-pressure turbine guider to the rear mounting edge of the combustion chamber casing through bolts, and screwing the bolts to be attached in advance;
hoisting the auxiliary device main body to the rear mounting edge of the low-pressure turbine guider of the engine through the hoisting ring;
inserting the precision positioning pin into a first precision positioning hole in the auxiliary device main body and a second precision positioning hole corresponding to the first precision positioning hole in the rear mounting edge of the low-pressure turbine guider at the same time;
fourthly, connecting the low-pressure turbine guider assembly coaxiality auxiliary control device and the low-pressure turbine guider into a whole by using a connecting bolt to penetrate through a first connecting hole in the auxiliary device main body;
and step five, taking a jumping value of the upper inner ring surface of the auxiliary device main body relative to the rotation central axis of the engine as a coaxiality judgment basis, and adjusting the coaxiality of the low-pressure turbine guider by adjusting a bolt between the front mounting edge of the low-pressure turbine guider and a combustion chamber casing.
Alternatively, in the fifth step, the jitter value is measured by a dial indicator or a dial indicator.
Alternatively, the dial indicator or the dial indicator is arranged on the high-pressure rotor of the engine through the indicator frame, and the rotation central axis of the dial indicator or the dial indicator is consistent with the rotation central axis of the engine.
Alternatively, in the first step, bolts are uniformly distributed at equal central angles on a circumference which is coaxial with the front mounting edge of the low-pressure turbine guider or the rear mounting edge of the combustor casing; and fifthly, sequentially screwing the bolts at the positions corresponding to the tail ends of the same crisscross lines according to a crisscross method, and in the screwing process, if the jumping value of the bolt is larger than the coaxiality requirement value, unscrewing the bolt, or screwing the bolt which is on the same straight line with the bolt and is positioned at the other end until the jumping value tends to zero.
As a choice, in the fifth step, the bolts are grouped, a plurality of consecutive adjacent bolts are each bolt group, and the number of bolts in different bolt groups is equal, the plurality of bolt groups are uniformly distributed at equal central angles on the circumference, four bolt groups are selected, the four bolt groups are located on the same cross line, the bolts in the bolt groups corresponding to the tail end of the cross line are sequentially screwed down according to the cross method, in the screwing process, if the jumping value of the position of the same bolt group is greater than the coaxiality requirement value, at least one bolt in the bolt group is unscrewed, or at least one bolt in the bolt group located on the same straight line and at the other end with the bolt group is screwed down until the jumping value tends to zero. It should be noted that the number of the connecting pieces of the joint surface is not limited by the cross-over method, and the situation that the bolts cannot be evenly grouped may occur in the present scheme, but only those bolt groups which are evenly divided are selected to be screwed according to the cross-over method, and redundant bolts are not grouped, so that the implementation of the present scheme is not affected.
Furthermore, the method for assembling the low-pressure turbine guider of the aircraft engine also comprises a sixth step,
when the four bolt groups selected in the step five are all screwed and the coaxiality meets the requirement, the corresponding positions of the other remaining bolt groups are matched by adopting an eccentric lining block and bolts;
when the four bolt sets selected in the step five are all screwed and the coaxiality is still not satisfactory, another four bolt sets on the same cross line are selected for adjustment again.
Alternatively, in the second step, the auxiliary device body is hoisted by a crane.
Compared with the prior art, the method can effectively guide the inspection of the control coaxiality and the final assembly coaxiality when the low-pressure turbine guide device is assembled.
Drawings
FIG. 1 is a schematic view of a low pressure turbine nozzle assembly concentricity auxiliary control device;
FIG. 2 is a schematic view of the main body of the auxiliary device;
FIG. 3 is a schematic view of a precision locating pin;
FIG. 4 is a schematic view of an auxiliary device connecting bolt;
FIG. 5 is a schematic view of the bail;
FIG. 6 is a schematic view of a bolt tightening method;
in the figure: 1. the auxiliary device comprises an auxiliary device main body, 2 precision positioning pins, 3 connecting bolts and 4 hanging rings.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
In the embodiment, the low-pressure turbine guider assembling coaxiality auxiliary control method is mainly realized by matching an auxiliary device with general tools such as a dial indicator (dial indicator). As shown in fig. 1 to 5, the assist device includes: the auxiliary device comprises an auxiliary device main body 1, a precision positioning pin 2, a connecting bolt 3 and a hanging ring 4.
The method for assembling the low-pressure turbine guider of the aircraft engine mainly comprises the following steps:
firstly, mounting an auxiliary device main body 1 to a rear mounting edge of a low-pressure turbine guider of an engine through a lifting ring 4 by using a crane;
secondly, the coaxiality of the inner ring surface of the auxiliary control device and the low-pressure turbine guider is ensured to be consistent by uniformly distributing the precise positioning pins 2 in the low-pressure turbine guider assembling coaxiality auxiliary control device;
connecting the auxiliary control device and the low-pressure turbine guider into a whole by using a connecting bolt 3;
step four, when the low-pressure turbine guider is installed, the coaxiality of the low-pressure turbine guider is adjusted by screwing down a bolt for connecting the lower end face (the front installation edge of the low-pressure turbine guider) and the combustion chamber casing;
and fifthly, mounting a dial indicator (dial indicator) on the high-pressure rotor of the engine through a dial indicator frame (the dial indicator frame or the dial indicator frame is fixed on the rotor of the engine, so that the dial indicator or the dial indicator is rotated by taking the rotation central axis of the engine as a rotation axis), and monitoring the inner ring surface jump of the auxiliary control device to judge whether the coaxiality of the low-pressure turbine guider meets the requirement. If the requirements are met, finishing the assembly control; and if the requirement is not met, continuing adjusting bolts of the front mounting edge of the low-pressure turbine guider and the combustor casing until the requirements are met.
Fig. 1 is a front view of a low-pressure turbine nozzle assembly coaxiality auxiliary control device, which mainly comprises an auxiliary device main body 1(1 piece) shown in fig. 2, a precision positioning pin 2(7 piece) shown in fig. 3, a connecting bolt 3(28 piece) shown in fig. 4 and a hanging ring 4(3 piece) shown in fig. 5.
The method for auxiliary control of the assembly coaxiality of the low-pressure turbine guider of the aircraft engine comprises the following specific implementation steps:
step one, mounting the low-pressure turbine guider on an engine host machine: the front mounting edge of the low-pressure turbine guider is connected to the rear mounting edge of the combustion chamber casing through 64 bolts, the bolts are screwed in advance to be attached, and the fact that the bolts are screwed in advance to be attached means that a fastener is guaranteed to generate pretightening force (tensile force) after being screwed for a few times, and meanwhile, the attachment of the mounting edge is guaranteed;
secondly, hoisting the auxiliary control device to the rear mounting edge of the low-pressure turbine guider by using a crane through a hoisting ring 4(3 pieces), wherein an inner ring surface for detecting coaxiality is arranged on the auxiliary device main body 1, and the precision (inner ring surface jumping value) of the inner ring surface is controlled within 0.02 mm;
step three, 7 second precision positioning holes are designed on the rear mounting edge of the low-pressure turbine guider, the rear mounting edge of the low-pressure turbine guider is simultaneously mounted into 7 first precision positioning holes on the auxiliary control device and 7 second precision positioning holes on the low-pressure turbine guider through the precision positioning pins 2(7 pieces), the position degree is controlled within 0.02mm, so as to ensure that the coaxiality of the inner ring surface of the auxiliary control device and the low-pressure turbine guider tends to be consistent, namely the radial run-out of the inner ring surface is controlled within 0.02mm through a reference A, a reference B and 7 first precision positioning holes (second precision positioning holes) on the end surface of the auxiliary device main body 1 in the graph 1, so that the inner ring surface is precise when being used as a reference for adjusting the coaxiality of the low-pressure turbine guider (the factors influencing the coaxiality of the inner ring surface and the low-pressure turbine guider include two aspects, one is the radial run-out when the inner ring surface is machined, and the other is the radial run-out when the inner ring surface is connected with the rear mounting edge of the low-pressure turbine guider, the former is controlled by a reference A and a reference B of the end face of the auxiliary device main body 1, and the latter is controlled by a precision positioning pin, a first precision positioning hole and a second precision positioning hole);
step four, fixedly mounting an auxiliary control device by using a connecting bolt 3(28 pieces) to ensure that the low-pressure turbine guider tends to be integrated;
installing a dial indicator frame (dial indicator frame) on a high-pressure rotor of the engine to enable the rotation center of the dial indicator to be consistent with that of the engine; the dial indicator head (micrometer head) contacts the inner ring surface of the auxiliary control device to measure circular run-out so as to judge whether the coaxiality of the low-pressure turbine guider meets the requirement of being not more than 0.05 mm;
sixthly, as shown in fig. 6, dividing each 4 bolts on the front mounting edge of the low-pressure turbine guide into 16 regions in total, applying a tightening torque from the region 1 after the bolts are attached, and loading the bolt torque of each region according to a cross method (as shown in fig. 6), wherein the regions 1, 2, 3 and 4 on the same cross line in fig. 6 are selected in the embodiment, the arrow direction in fig. 6 is the tightening sequence, namely 1 → 2 → 3 → 4, and if the coaxiality does not meet the requirement after the 4 regions are tightened, continuing to adjust according to 5 → 6 → 7 → 8;
and step seven, in the process of loading the torque, observing the needle placing and pressure gauge conditions of each area dial gauge (namely, the dial gauge or the dial gauge rotates around the rotation central axis of the engine to measure the bounce value of the inner ring surface, and the rotation central axis of the engine is used as the reference of the coaxiality of the engine). For example: if the area 3 is pressed by the gauge to exceed more than 0.05mm, applying small moment to the area 4 or unscrewing the area 3 to enable the gauge needle to be close to the point 0; by parity of reasoning, loading the bolt torque of each region respectively until screwing down;
step eight, reading circular runout after screwing, and if the circular runout is within 0.05mm, placing eccentric lining blocks and bolts to limit circumferential change of the low-pressure turbine guider (the eccentric lining blocks are used for preventing the bolts from loosening and other anti-loosening structures can be adopted) in 10 holes which are left and uniformly distributed on the front mounting edge of the low-pressure turbine guider (firstly, the cross method is adopted for screwing 1 → 2 → 3 → 4, and then 5 → 6 is adopted, so that 10 bolt holes are left), so as to ensure that the coaxiality of the low-pressure turbine guider meets the requirement;
step nine, if the circular runout exceeds 0.05mm, repeating the work of the step six to the step eight until the final circular runout reaches the design requirement of 0.05 mm.
Claims (7)
1. The method for assembling the low-pressure turbine guider of the aircraft engine is characterized by comprising the following steps of: assembling a coaxiality auxiliary control device by adopting a low-pressure turbine guider, wherein the auxiliary control device comprises,
the auxiliary device comprises an auxiliary device body (1), wherein the auxiliary device body (1) is a circular ring, an inner ring surface coaxial with the auxiliary device body (1) is arranged on the auxiliary device body (1), and a plurality of first precise positioning holes, first connecting holes and second connecting holes which are parallel to the axial direction of the auxiliary device body (1);
the precise positioning pin (2), the precise positioning pin (2) is inserted into a first precise positioning hole on the auxiliary device main body (1) and a second precise positioning hole on the rear mounting edge of the low-pressure turbine guider;
the connecting bolt (3), the said connecting bolt (3) is connected with the first connecting hole on the auxiliary device body (1);
the lifting ring (4), the lifting ring (4) is connected with a second connecting hole in the auxiliary device main body (1);
the assembly method comprises the following steps of,
connecting the front mounting edge of the low-pressure turbine guider to the rear mounting edge of the combustion chamber casing through bolts, and screwing the bolts to be attached in advance;
hoisting the auxiliary device main body (1) to the rear mounting edge of the low-pressure turbine guider of the engine through the hoisting ring (4);
simultaneously inserting the precision positioning pin (2) into a first precision positioning hole in the auxiliary device main body (1) and a second precision positioning hole corresponding to the first precision positioning hole in the rear mounting edge of the low-pressure turbine guider;
fourthly, a connecting bolt (3) penetrates through a first connecting hole in the auxiliary device main body (1) to connect the low-pressure turbine guider assembly coaxiality auxiliary control device and the low-pressure turbine guider into a whole;
and step five, taking a jumping value of the upper inner ring surface of the auxiliary device main body (1) relative to the rotation central axis of the engine as a coaxiality judgment basis, and adjusting the coaxiality of the low-pressure turbine guider by adjusting a bolt between the front mounting edge of the low-pressure turbine guider and a combustion chamber casing.
2. The aircraft engine low pressure turbine nozzle assembly method of claim 1, wherein: and in the fifth step, measuring the jitter value through a dial indicator or a dial indicator.
3. The aircraft engine low pressure turbine nozzle assembly method of claim 2, wherein: the dial indicator or the dial indicator is arranged on the high-pressure rotor of the engine through the indicator frame, and the rotation central axis of the dial indicator or the dial indicator is consistent with the rotation central axis of the engine.
4. The aircraft engine low pressure turbine nozzle assembly method of claim 1, wherein:
in the first step, bolts are uniformly distributed at equal central angles on the circumference which is coaxial with the front mounting edge of the low-pressure turbine guider or the rear mounting edge of the combustion chamber casing;
and fifthly, sequentially screwing the bolts at the positions corresponding to the tail ends of the same crisscross lines according to a crisscross method, and in the screwing process, if the jumping value of the bolt is larger than the coaxiality requirement value, unscrewing the bolt, or screwing the bolt which is on the same straight line with the bolt and is positioned at the other end until the jumping value tends to zero.
5. The aircraft engine low pressure turbine nozzle assembly method of claim 4, wherein:
and fifthly, grouping the bolts, wherein a plurality of continuous adjacent bolts are each bolt group, the bolts in different bolt groups are equal in number, the bolt groups are uniformly distributed at equal central angles on the circumference, selecting four bolt groups, the four bolt groups are positioned on the same cross line, sequentially screwing the bolts in the bolt groups corresponding to the tail ends of the cross line according to a cross method, and in the screwing process, if the jumping value of the position of the same bolt group is greater than the coaxiality requirement value, unscrewing at least one bolt in the bolt group, or screwing at least one bolt in the bolt group which is positioned on the same straight line and at the other end with the bolt group until the jumping value tends to zero.
6. The aircraft engine low pressure turbine nozzle assembly method of claim 5, wherein: the method also comprises a sixth step of,
when the four bolt groups selected in the step five are all screwed and the coaxiality meets the requirement, the corresponding positions of the other remaining bolt groups are matched by adopting an eccentric lining block and bolts;
when the four bolt sets selected in the step five are all screwed and the coaxiality is still not satisfactory, another four bolt sets on the same cross line are selected for adjustment again.
7. The aircraft engine low pressure turbine nozzle assembly method of claim 1, wherein: and in the second step, the auxiliary device main body (1) is hoisted through a crane.
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| CN202110430012.8A CN113199237B (en) | 2021-04-21 | 2021-04-21 | Method for assembling low-pressure turbine guider of aircraft engine and coaxiality auxiliary control device |
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| CN202110430012.8A CN113199237B (en) | 2021-04-21 | 2021-04-21 | Method for assembling low-pressure turbine guider of aircraft engine and coaxiality auxiliary control device |
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| CN118003074B (en) * | 2024-04-10 | 2024-06-07 | 苏州中科科仪技术发展有限公司 | Centering assembly device and method for turbine and dynamic traction cylinder and application |
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