CN107576293B - Cantilever fulcrum bounce detection tool and detection method - Google Patents
Cantilever fulcrum bounce detection tool and detection method Download PDFInfo
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- CN107576293B CN107576293B CN201710942549.6A CN201710942549A CN107576293B CN 107576293 B CN107576293 B CN 107576293B CN 201710942549 A CN201710942549 A CN 201710942549A CN 107576293 B CN107576293 B CN 107576293B
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Abstract
The invention discloses a cantilever fulcrum run-out detection tool and a detection method, wherein the detection tool is clamped on a turbine casing to be used for detecting a run-out value and a blade tip gap of a low-pressure turbine rotor positioned at a cantilever end of a gas compressor, the low-pressure turbine rotor is fixed through a measuring bridge, the run-out value and the blade tip gap of the low-pressure turbine rotor are detected by utilizing the gap on the measuring bridge and combining an external detection device, and cantilever deflection at the low-pressure turbine can be avoided by adding an auxiliary supporting point to the low-pressure turbine rotor during engine assembly, so that the measured data is more accurate. In addition, the defect that the interstage guider cannot be checked during installation is overcome, the low-pressure turbine rotor is effectively fixed, and the problem that deflection occurs at the supporting point of the low-pressure turbine rotor and accurate detection cannot be achieved is solved.
Description
Technical Field
The invention relates to the field of aircraft engine assembly, in particular to a cantilever fulcrum bounce detection tool and a cantilever fulcrum bounce detection method.
Background
The low-pressure rotor of a novel turboprop engine comprises a three-stage axial-flow compressor which is connected with a single-stage turbine through a long shaft. As shown in fig. 1, the compressor and turbine are mounted on the shaft with short cylindrical locations, and the low pressure compressor rotor 10 and low pressure turbine rotor 8 are supported on A, B and bearing number C of the engine in a 1-1-1 support. The low-pressure turbine extends outwards from a cantilever of the low-pressure compressor and is fixed with the low-pressure compressor through a spline pull rod shaft and a locking nut. Wherein the bearing inner ring C is mounted on the low-pressure turbine rotor 8, and the bearing outer ring C is mounted in the casing of the interstage guider 9. When the engine is assembled, the interstage guide 9 assembly with the bearing outer ring is installed into the engine, the inner ring and the outer ring of the bearing C are matched, and the low-pressure turbine rotor 8 is fixed, wherein the structure is shown in figure 2.
Before the inter-stage guider 9 is assembled, the end face runout T1 and the radial runout S1 and S2 of the low-pressure turbine rotor 8 and the clearance N2 between the tip of the low-pressure turbine rotor 8 and the outer ring of the casing matched with the low-pressure turbine rotor need to be checked to judge whether the low-pressure turbine rotor is qualified, but after the inter-stage guider 9 is assembled, the end face runout and the tip clearance to be detected by the low-pressure turbine rotor 8 are blocked by the casing of the inter-stage guider 9, and the meter frame cannot enter so that the end face runout value and the tip clearance cannot be checked.
The existing detection generally detects the end face runout value and the blade tip clearance of a low-pressure turbine rotor 8 when an interstage guider 9 is not installed, but if the interstage guider 9 is not installed, the low-pressure turbine rotor 8 is connected with a low-pressure compressor through a long shaft, a supporting point of the low-pressure turbine rotor 8 is not fixed by a bearing outer ring on the interstage guider 9, cantilever deflection occurs at the supporting point, the measured runout value and the blade tip clearance of the low-pressure turbine rotor 8 are not accurate, in addition, when the 45-degree state of an engine is detected, the low-pressure turbine rotor 8 sinks, the blade tip and a casing outer ring can be scratched in the process of rotating the rotor, and the runout value and the blade tip clearance cannot be accurately detected.
Therefore, in view of the above problems, it is desirable to design an apparatus and method capable of accurately detecting a low-pressure turbine rotor runout value and a blade tip clearance.
Disclosure of Invention
The invention provides a cantilever fulcrum run-out detection tool and a cantilever fulcrum run-out detection method, and aims to solve the technical problem that an accurate run-out value and a blade tip clearance cannot be obtained when a turbine rotor is detected on an end face.
The technical scheme adopted by the invention is as follows:
the utility model provides a cantilever fulcrum is beated and is detected frock for the clamping is in order to detect the value of beating and the apex clearance that is located the low pressure turbine rotor of compressor low-pressure shaft cantilever end to turbine casket, and it includes to detect the frock: the measuring bridge is fixed on the turbine casing and is used for being matched with an external detection device to detect the runout value of the low-pressure turbine rotor and the blade tip clearance, and the measuring bridge is provided with a fixing piece for fixing the low-pressure turbine rotor;
the measuring bridge comprises: the outer ring mounting seat is used for fixing the measuring bridge on the turbine casing, the inner ring mounting seat used for fixing the fixing piece is arranged inside the outer ring mounting seat, the inner ring mounting seat and the outer ring mounting seat are connected through a plurality of supporting rods, and an external detection device is convenient to detect the jumping value and the blade tip gap of the low-pressure turbine rotor from the gap formed among the supporting rods, the inner ring mounting seat and the outer ring mounting seat.
Further, the fixing member is a bearing outer ring that is fitted with a bearing inner ring provided on the low-pressure turbine rotor.
Further, the detection tool further comprises a pressing plate used for pressing the bearing outer ring.
Furthermore, a plurality of first threaded holes are formed in the circumferential direction of the pressure plate at intervals, and second threaded holes are formed in the inner ring mounting seat corresponding to the first threaded holes; the bearing outer ring is fixed on the inner ring mounting seat through a first bolt penetrating through the first threaded hole and the second threaded hole.
Further, the outer ring mounting base is fixed on the turbine casing through a second bolt.
Furthermore, a threaded hole corresponding to the second bolt is formed in the outer ring mounting seat at a position corresponding to the fixing position of the interstage guider and the turbine casing, so that the measuring bridge can be conveniently mounted on the turbine casing.
Furthermore, 3 support rods are uniformly distributed between the inner ring mounting seat and the outer ring mounting seat.
According to another aspect of the present invention, there is also provided a detection method using the above-mentioned cantilever fulcrum bounce detection tool, the method including the steps of:
mounting a fixing member for fixing a low-pressure turbine rotor to the measuring bridge;
mounting the metering bridge on the turbine casing;
the external detection device detects the runout value and the blade tip clearance of the low-pressure turbine rotor by utilizing the space formed among the upper inner ring mounting seat, the outer ring mounting seat and the connecting rod of the measuring bridge.
The invention has the following beneficial effects:
the detection tool is clamped on the turbine casing to detect the jumping value and the tip clearance of the low-pressure turbine rotor positioned at the cantilever end of the gas compressor, the low-pressure turbine rotor is fixed through the flux bridge, the jumping value and the tip clearance of the low-pressure turbine rotor are detected by utilizing the clearance on the flux bridge and combining an external detection device, and cantilever deflection at the low-pressure turbine can be avoided by adding an auxiliary supporting point to the low-pressure turbine rotor during engine assembly, so that the measured data is more accurate. In addition, the defect that the interstage guider cannot be checked during installation is overcome, the low-pressure turbine rotor is effectively fixed, and the problem that deflection occurs at the supporting point of the low-pressure turbine rotor and accurate detection cannot be achieved is solved.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a prior art low pressure spool support structure of a turboprop;
FIG. 2 is a schematic structural view of a prior art low pressure turbine rotor equipped with interstage guides;
FIG. 3 is a schematic cross-sectional view of a metering bridge of a preferred embodiment of the present invention;
FIG. 4 is a top view of a metering bridge of a preferred embodiment of the present invention;
fig. 5 is a schematic diagram of the cantilever fulcrum bounce detection tool in the preferred embodiment of the invention.
The reference numbers illustrate:
1. a metering bridge; 101. an outer ring mounting seat; 102. an inner ring mounting seat; 103. a connecting rod; 2. pressing a plate; 3. a first bolt; 4. a bearing outer ring; 5. a bearing inner ring; 6. a turbine case; 7. a second bolt; 8. a low pressure turbine rotor; 9. an interstage deflector; 10. a low pressure compressor rotor.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1, the preferred embodiment of the present invention provides a cantilever fulcrum bounce detection tool, and a method for detecting a low-pressure turbine rotor bounce value and a blade tip clearance on an existing engine is to detect the low-pressure turbine rotor bounce value and the blade tip clearance without installing an interstage guider 9, but the following disadvantages may occur: on one hand, because the low-pressure turbine rotor 8 is connected with the low-pressure compressor through the long shaft, cantilever deflection can occur during end face detection and blade tip gap detection under the condition that the supporting point of the low-pressure turbine rotor 8 is not fixed, so that the measured low-pressure turbine rotor runout value and blade tip gap have deviation, and the measurement result is inaccurate; on the other hand, when the engine rotates for 45 degrees for detection, the low-pressure turbine rotor 8 sinks, and in the process of rotating the rotor, the blade tip and the outer ring of the casing are hung and wiped, so that the measurement result is inaccurate. However, if the interstage guide 9 assembly is installed in an engine and the low-pressure turbine rotor 8 is fixed, cantilever deflection of the supporting point of the low-pressure turbine rotor 8 cannot occur, but after the interstage guide 9 is assembled, the end face and the blade tip clearance of the low-pressure turbine rotor 8 are blocked by the casing of the interstage guide 9, and a measurement gauge stand cannot enter for inspection. In view of the above problems, an embodiment of the present invention provides a cantilever fulcrum bounce detection tool, which is used for being clamped to a turbine casing to detect a bounce value and a blade tip gap of a low-pressure turbine rotor located at a cantilever end of a low-pressure shaft of a gas compressor.
Referring to fig. 3 and 4, the detection tool of the present embodiment includes: fix on turbine casket 6 be used for with external detection device cooperation in order to detect the runout value of low pressure turbine rotor 8 and the volume bridge 1 in apex clearance, be equipped with the mounting that is used for fixed low pressure turbine rotor 8 on the volume bridge 1, volume bridge 1 includes: an outer ring mounting seat 101 for fixing the measuring bridge 1 on the turbine casing 6, an inner ring mounting seat 102 for fixing a fixing piece is arranged inside the outer ring mounting seat 101, and the inner ring mounting seat 102 and the outer ring mounting seat 101 are connected through a plurality of connecting rods 103.
In the embodiment, the fixing part is a bearing outer ring 4 matched with a bearing inner ring 5 arranged on the low-pressure turbine rotor 8, the bearing outer ring 4 is fixed through an inner ring mounting seat 102, and then the measuring bridge 1 assembled with the bearing outer ring 4 is clamped on the turbine casing 6, so that the low-pressure turbine rotor 8 is fixed; the external detection device detects the end face runout T1, the radial runout S1 and S2 of the low-pressure turbine rotor 8 and the gap N2 between the blade tip of the low-pressure turbine rotor and the outer ring of the turbine casing 6 through the gaps formed among the inner ring mounting seat 102, the outer ring mounting seat 101 and the connecting rod 103. The low-pressure turbine rotor 8 is fixed through the flux bridge 1, cantilever deflection cannot occur at a supporting point of the low-pressure turbine rotor 8, and hanging friction does not exist between the blade tip and the outer ring of the turbine casing 6 when the engine is rotated, so that a runout value and a blade tip gap can be accurately measured.
The cantilever fulcrum of this embodiment beats and detects frock, the volume bridge that utilizes the director between the simulation stage fixes the low pressure turbine rotor, and there is the detection device that the clearance combines external on the volume bridge to detect the value of beating and the apex clearance of low pressure turbine rotor, has avoided the unable drawback of examining of director between the installation stage, and the effectual low pressure turbine rotor that has fixed has solved the low pressure turbine rotor and has taken place the beat and the problem that can't the accurate detection in low pressure turbine rotor supporting point.
Preferably, the detection tool further comprises a pressing plate 2 for pressing the bearing outer ring 4, and the pressing plate 2 is fixed on the inner ring mounting seat 102 through a first bolt 3. In this embodiment, a plurality of first threaded holes matched with the first bolts 3 are arranged at intervals in the circumferential direction of the pressing plate 2, second threaded holes are arranged at positions corresponding to the first threaded holes on the inner ring mounting seat 102, specifically, the inner ring mounting seat 102 tightly clamps the bearing outer ring 4, the pressing plate 2 tightly presses, and the first bolts 3 pass through the first threaded holes and the second threaded holes to fix the bearing outer ring 4 on the inner ring mounting seat 102.
Referring to fig. 5, a plurality of screw holes are provided on the circumference of the outer ring mount 101 at positions corresponding to the positions where the inter-stage guide 9 is fitted to the turbine casing 6, and the outer ring mount 101 is fixed to the turbine casing 6 by the second bolts 7, thereby fitting the bearing inner ring 5 and the bearing outer ring 4. In the embodiment, the metering bridge 1 is clamped on the turbine casing 6 by simulating the size of the interstage guider 9 of the metering bridge 1, so that the condition that a mounting hole for fixing the metering bridge 1 is additionally formed in the turbine casing 6 is avoided, the low-pressure turbine rotor 8 is effectively fixed, the whole low-pressure rotor is supported and fixed on the casing, the rotary engine is in a 45-degree state, the clearance among the bearings is eliminated, and the jumping values T1, S1, S2 and the blade tip clearance N2 are checked by utilizing the clearance formed among the inner ring mounting seat 102, the outer ring mounting seat 101 and the connecting rod 103 on the metering bridge 1 and combining with an external detection device. After the inspection, the measuring bridge 1 is unloaded and then loaded into the interstage guide 9.
Preferably, there are 3 connecting rods 103 evenly distributed between the inner ring mount 102 and the outer ring mount 101. In the present embodiment, a space hole in the circumferential direction of the measuring bridge 1 is formed between the connecting rod 103, the inner ring mount 102, and the outer ring mount 101, and the meter rack of the measuring device measures the runout value and the blade tip clearance of the low-pressure turbine rotor 8 through the space hole.
The operating principle of the cantilever fulcrum bounce detection tool of the embodiment is as follows: firstly, the bearing outer ring 4 is installed on the inner ring installation seat 102, the pressing plate 2 is used for pressing and the first bolt 3 is used for fixing, then the measuring bridge 1 provided with the bearing outer ring 4 is installed on the turbine casing 6, the bearing outer ring 4 is matched with the bearing inner ring 5, the low-pressure turbine rotor 8 is effectively fixed, the whole low-pressure turbine rotor 8 is supported and fixed on the turbine casing 6 through the measuring bridge 1, then the engine rotates for 45 degrees, the clearance between the bearings is convenient to eliminate, and the bounce value and the blade tip clearance of the low-pressure turbine rotor 8 are detected by utilizing a detection device which is formed among the inner ring installation seat 102, the outer ring installation seat 101 and the connecting rod 103 on the measuring bridge 1 and is combined with the outside space hole.
The invention also provides a method for detecting the runout value and the blade tip clearance of the low-pressure turbine rotor by using the cantilever fulcrum runout detection tool, which comprises the following steps:
firstly, a bearing outer ring 4 matched with a bearing inner ring 5 is installed on a measuring bridge 1;
secondly, the metering bridge 1 is mounted on the turbine casing 6; specifically, the outer ring mount 101 is provided with a threaded hole that engages with the second bolt 7 at a position corresponding to the position where the interstage guide 9 is fitted to the turbine casing 6, so that it is not necessary to provide a mounting hole that engages with the measuring bridge 1 on the turbine casing 6, and the measuring bridge 1 is mounted to the turbine casing 6 in accordance with the method of fitting the interstage guide 9.
Then, the external detection device checks the runout value and the tip clearance of the low-pressure turbine rotor 8 using the clearance formed between the inner ring mount 102, the outer ring mount 101, and the link 103 on the measuring bridge 1.
According to the method for detecting the runout value and the blade tip clearance of the low-pressure turbine rotor, the measuring bridge is fixed on the turbine casing according to the assembling method of the interstage guider so as to effectively fix the low-pressure turbine rotor, the runout value and the blade tip clearance of the low-pressure turbine rotor are detected by utilizing the circumferential clearance on the measuring bridge, the defect that the interstage guider cannot be detected when the interstage guider is installed is avoided, and the problem that the supporting point of the low-pressure turbine rotor cannot be accurately detected due to deflection is solved.
From the above description it can be seen that: according to the cantilever fulcrum bounce detection tool and the detection method, the low-pressure turbine rotor is fixed by the utilization of the measuring bridge, the bounce value of the low-pressure turbine rotor and the blade tip clearance are detected by the utilization of the clearance on the measuring bridge in combination with an external detection device, and the cantilever deflection at the low-pressure turbine can be avoided by adding the auxiliary supporting point to the low-pressure turbine rotor during the assembly of the engine, so that the measured data are more accurate. In addition, the defect that the interstage guider cannot be checked during installation is overcome, the low-pressure turbine rotor is effectively fixed, and the problem that deflection occurs at the supporting point of the low-pressure turbine rotor and accurate detection cannot be achieved is solved.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. The utility model provides a cantilever fulcrum is beated and is detected frock for the value of beating and apex clearance in order to detect the low pressure turbine rotor (8) that is located compressor low-pressure shaft cantilever end on clamping to turbine casket (6), its characterized in that, it includes to detect the frock: the measuring bridge (1) is fixed on the turbine casing (6) and is used for being matched with an external detection device to detect the runout value and the blade tip clearance of the low-pressure turbine rotor (8), and a fixing piece for fixing the low-pressure turbine rotor (8) is arranged on the measuring bridge (1);
the metering bridge (1) comprises: an outer ring mounting seat (101) used for fixing the measuring bridge (1) on the turbine casing (6), an inner ring mounting seat (102) used for fixing the fixing piece is arranged inside the outer ring mounting seat (101), the inner ring mounting seat (102) is connected with the outer ring mounting seat (101) through a plurality of supporting rods (103), and an external detection device can detect the jumping value and the blade tip gap of the low-pressure turbine rotor (8) from the gap formed among the supporting rods (103), the inner ring mounting seat (102) and the outer ring mounting seat (101);
the fixing piece is a bearing outer ring (4) matched with a bearing inner ring (5) arranged on the low-pressure turbine rotor (8), the bearing outer ring (4) is fixed through an inner ring mounting seat (102), and then a measuring bridge (1) assembled with the bearing outer ring (4) is clamped on a turbine casing (6), so that the low-pressure turbine rotor (8) is fixed; an external detection device detects the end face runout T1, the radial runout S1 and S2 of the low-pressure turbine rotor (8) and the gap N2 between the blade tip of the low-pressure turbine rotor and the outer ring of the turbine casing (6) through the gaps formed among the inner ring mounting seat (102), the outer ring mounting seat (101) and the connecting rod (103); the low-pressure turbine rotor (8) is fixed through the flux bridge (1), cantilever deflection cannot occur at a supporting point of the low-pressure turbine rotor (8), and hanging friction does not exist between the blade tip and the outer ring of the turbine casing (6) when the engine is rotated, so that a bounce value and a blade tip gap can be accurately measured;
the detection tool further comprises a pressing plate (2) used for pressing the bearing outer ring (4), and the pressing plate (2) is fixed on the inner ring mounting seat (102) through a first bolt (3); a plurality of first threaded holes matched with the first bolts (3) are formed in the circumferential direction of the pressing plate (2) at intervals, second threaded holes are formed in positions, corresponding to the first threaded holes, on the inner ring mounting seat (102), the inner ring mounting seat (102) tightly clamps the bearing outer ring (4), the pressing plate (2) tightly presses the bearing outer ring, and the first bolts (3) penetrate through the first threaded holes and the second threaded holes to fix the bearing outer ring (4) on the inner ring mounting seat (102);
a plurality of threaded holes are formed in the circumference of the outer ring mounting seat (101) at positions corresponding to the positions where the interstage guiders (9) are assembled to the turbine casing (6), and the outer ring mounting seat (101) is fixed on the turbine casing (6) through second bolts (7), so that the bearing inner ring (5) is matched with the bearing outer ring (4); the measuring bridge (1) simulates the size of an interstage guider (9) to clamp the measuring bridge (1) to a turbine casing (6), a mounting hole for fixing the measuring bridge (1) is avoided being formed in the turbine casing (6), a low-pressure turbine rotor (8) is effectively fixed, the whole low-pressure turbine rotor (8) is supported and fixed on the turbine casing, the rotary engine is in a 45-degree state and is eliminated, and a gap formed among an inner ring mounting seat (102), an outer ring mounting seat (101) and a connecting rod (103) on the measuring bridge (1) is combined with an external detection device to check a jumping value T1, S1, S2 and a blade tip gap N2.
2. The cantilever fulcrum run-out detection tool of claim 1,
the number of the supporting rods (103) is 3, and the supporting rods are uniformly distributed between the inner ring mounting seat (102) and the outer ring mounting seat (101).
3. The detection method for the cantilever fulcrum bounce detection tool according to any one of the claims 1 to 2 is characterized by comprising the following steps of:
mounting the fixing for fixing the low-pressure turbine rotor (8) to the measuring bridge (1);
mounting the metering bridge (1) on the turbine casing (6);
and the external detection device utilizes the space formed among the inner ring mounting seat (102), the outer ring mounting seat (101) and the connecting rod (103) on the measuring bridge (1) to check the runout value and the blade tip clearance of the low-pressure turbine rotor (8).
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| CN110763180B (en) * | 2019-11-06 | 2021-05-07 | 中国航发南方工业有限公司 | Method for measuring dimension of small step surface of slender shaft of cantilever |
| CN114046203B (en) * | 2021-11-10 | 2022-12-09 | 中国航发南方工业有限公司 | Assembling method for rotor fulcrum of certain type turbofan engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59220609A (en) * | 1983-05-30 | 1984-12-12 | Nissan Motor Co Ltd | Clearance measuring method during turbine operation |
| CN102967270A (en) * | 2012-11-14 | 2013-03-13 | 西南科技大学 | Method and system for measuring engine tip clearance |
| CN204195185U (en) * | 2014-11-06 | 2015-03-11 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine low-pressure turbine assembling detection device |
| CN106679551A (en) * | 2017-01-23 | 2017-05-17 | 中国航发沈阳发动机研究所 | Gland and intermediate case concentricity measurement method and measurement tool |
-
2017
- 2017-10-11 CN CN201710942549.6A patent/CN107576293B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59220609A (en) * | 1983-05-30 | 1984-12-12 | Nissan Motor Co Ltd | Clearance measuring method during turbine operation |
| CN102967270A (en) * | 2012-11-14 | 2013-03-13 | 西南科技大学 | Method and system for measuring engine tip clearance |
| CN204195185U (en) * | 2014-11-06 | 2015-03-11 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine low-pressure turbine assembling detection device |
| CN106679551A (en) * | 2017-01-23 | 2017-05-17 | 中国航发沈阳发动机研究所 | Gland and intermediate case concentricity measurement method and measurement tool |
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