CN108817815A - The one stage diverter fixture of gas turbine of aero-engine - Google Patents

The one stage diverter fixture of gas turbine of aero-engine Download PDF

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Publication number
CN108817815A
CN108817815A CN201810924093.5A CN201810924093A CN108817815A CN 108817815 A CN108817815 A CN 108817815A CN 201810924093 A CN201810924093 A CN 201810924093A CN 108817815 A CN108817815 A CN 108817815A
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CN
China
Prior art keywords
support
blade
inner ring
ring
support frame
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201810924093.5A
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Chinese (zh)
Inventor
吴鸣耀
赖能红
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Changzhou Hangfa China Lanxiang Machinery LLC
Original Assignee
Changzhou Hangfa China Lanxiang Machinery LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Changzhou Hangfa China Lanxiang Machinery LLC filed Critical Changzhou Hangfa China Lanxiang Machinery LLC
Priority to CN201810924093.5A priority Critical patent/CN108817815A/en
Publication of CN108817815A publication Critical patent/CN108817815A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
    • 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
    • B23P13/00—Making metal objects by operations essentially involving machining but not covered by a single other subclass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
    • B25B11/02—Assembly jigs

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to a kind of one stage diverter fixtures of gas turbine of aero-engine, before being welded to blade and inner ring, gap location pad dress and the matched gasket of gap shape between inner ring and blade trailing edge, the deformation for preventing inner ring and outer ring when because of welding, impacts the gap of blade trailing edge and interior interannular；After the completion of outer ring and blade are welded and fixed, before carrying out aging strengthening model, support fixture is installed close to inner ring endface inside outer ring, prevents from shrinking compression blade component because of outer ring, influences the gap between blade trailing edge and inner ring.Concave surface is opposite when support fixture includes the first support frame, the second support frame, uses and the symmetrically arranged semiorbicular support ring of a pair, the whole support component in bar shaped is formed after first support frame, the second support frame are mating, the both ends of the support component are mating with the middle inside of a pair of of support ring respectively, it is assemblied in inside the outer ring of one stage diverter of gas turbine close to inner ring endface, forms support.

Description

The one stage diverter fixture of gas turbine of aero-engine
Technical field
The present invention relates to aero-engine turbine guide device mounting technology fields, the specifically gas turbine of aero-engine One stage diverter fixture.
Background technique
Such as Fig. 1 to Fig. 3, in aero-engine turbine guide device technical field, one stage diverter of gas turbine generally by Inner ring 1 and outer ring 2 form runner, and blade 3 and blade trailing edge 4 are fixedly linked and form blade assembly, lead between inner ring 1 and outer ring 2 Multiple blade assemblies are crossed to be connected；Existing one stage diverter of gas turbine be first blade 3 and blade trailing edge 4 are fixedly linked, then Blade 3 is plugged in the blade profile hole of inner ring 1 and outer ring 2, then blade 3 is fixed on gas turbine level-one by welding In the inner ring 1 and outer ring 2 of guider, and there are certain gap 5 between blade trailing edge 4 and inner ring 1, the width in gap 5 is 0.3mm to 0.5mm.
Since nozzle ring is in severe working environment, high-temperature fuel gas stream should be born and each part uneven heating is drawn The biggish thermal stress risen, expands with heat and contract with cold serious, bears combustion gas again and passes through the aerodynamic force generated when guide vane and by gas The caused oscillating load of stream pulsation, so there are strict requirements in the gap 5 between blade trailing edge 4 and inner ring 1, gap is excessive Guiding efficiency is influenced, blade is contacted with inner ring under the too small hot environment in gap, causes accident.
Existing one stage diverter assembly method of gas turbine is as follows：
A. blade and blade trailing edge are fixedly linked, form blade assembly；
B. the blade profile hole in inner ring and outer rings is polished, both ends of the blade is inserted into the leaf of respective leaves type hole in inner ring and outer rings respectively Basin；There are gaps between blade trailing edge and inner ring at this time；
C. blade and inner ring are welded and fixed；
D. blade and outer ring are welded and fixed；
E. aging strengthening model is carried out, one stage diverter of gas turbine is obtained after the completion and goes forward side by side performing check.
In assembling process, since inner ring and outer rings are all thin-wall parts, it is easy contraction distortion in welding, leads to leaf The gap of piece trailing edge and inner ring changes, when carrying out aging strengthening model, also due to the contraction compression blade component of outer ring, Also it will affect the gap between blade trailing edge and inner ring, cause to assemble unqualified, first-time qualification rate is only 60%.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of combustions that may insure gap between blade trailing edge and inner ring Between one stage diverter assembly method of air turbine and the guider prevent between blade trailing edge and inner ring in aging strengthening model The support fixture of gap variation.
To solve the above-mentioned problems, the present invention provides a kind of one stage diverter assembly methods of gas turbine, including：
A. blade and blade trailing edge are fixedly linked, form blade assembly.
B. the blade profile hole in inner ring and outer rings is polished, respective leaves type hole in inner ring and outer rings is inserted at the both ends of blade respectively Leaf basin in；There are gaps between blade trailing edge and inner ring at this time.
C. it is packed into gasket in the gap of inner ring and blade trailing edge, blade and inner ring is welded and fixed.
D. blade and outer ring are welded and fixed；The gasket between the blade trailing edge and inner ring is removed after the completion.
E. support fixture is installed close to the inner ring endface inside the outer ring.
F. aging strengthening model is carried out, takes out support fixture after the completion, one stage diverter of gas turbine is obtained and goes forward side by side performing check.
Further, gasket described in step B is 1Cr18Ni9Ti gasket, and intensity is high, and be easy to extend processing, cheap, Gap shape between the shape of the gasket and the blade trailing edge and the inner ring matches, and considers the receipts of subsequent heat treatment Compression deformation, the gasket weld with a thickness of 0.4mm to 0.6mm greater than the upper limit in gap between the blade trailing edge and inner ring When play a supportive role to the gap between inner ring and blade trailing edge, it is possible to prevente effectively from the outer ring, inner ring welding when receipts Compression deformation impacts the gap.
Further, in step C, before the blade and the inner ring are welded and fixed, first by blade and inner ring Positioning welding is carried out, then soldering test part and is detected, the blade and the inner ring are carried out again after part detection to be tested is qualified Welding, it is ensured that welding effect.
Further, in step D, before the blade and the outer ring are welded and fixed, first by blade and outer ring Positioning welding is carried out, then soldering test part and is detected, the blade and the outer ring are carried out again after part detection to be tested is qualified Welding, it is ensured that welding effect.
Support fixture in above-mentioned one stage diverter assembly method of gas turbine, including the first support frame, the second support Frame, concave surface is opposite when using and the symmetrically arranged semiorbicular support ring of a pair, and the first support frame, the second support frame are mating The whole support component in bar shaped is formed afterwards, and the both ends of the support component are matched with the middle inside grafting of a pair of of support ring respectively It closes, the support ring is connected into a support fixture, be assemblied in inside the outer ring of one stage diverter of gas turbine close to inner ring Endface, the outer diameter of the support fixture is identical close to the internal diameter of inner ring endface as inside the outer ring, forms support, reduces The contraction of outer ring described in heat treatment and cooling procedure, avoid blade trailing edge described in the effect of contraction because of outer ring and the inner ring it Between gap size.
Further, the support ring middle inside protrusion setting interconnecting piece, the interconnecting piece be equipped with groove, for into Row grafting, structure is simple, is easily assembled.
Further, one end of first support frame is equipped with protrusion, and the other end is equipped with jack, second support frame One end is again provided with protrusion, and the other end of second support frame is mating in the jack of first support frame, institute It is mating in the groove of the support ring interconnecting piece to state protrusion；First, second support frame described in when use passes through jack Grafting is connected, and the protrusion is mating with the groove on the interconnecting piece of two support rings respectively, and the support ring is connected At an entirety.
The technical effect of invention：（1）One stage diverter assembly method of gas turbine of the invention, compared with the existing technology, In one stage diverter assembling process of gas turbine, before being welded to blade and inner ring, between inner ring and blade trailing edge Gap location pad dress and the matched gasket of gap shape, when welding play a supportive role to the gap between inner ring and blade trailing edge, The deformation for preventing inner ring and outer ring when because of welding, impacts gap size；（2）Completion is welded and fixed in outer ring and blade Afterwards, before carrying out aging strengthening model, support fixture is installed close to inner ring endface in the outer ring of guider, is prevented because of outer ring heat Compression blade component is shunk when processing, influences the gap between blade trailing edge and inner ring；（3）Gasket with a thickness of 0.4mm extremely 0.6mm, for the contraction distortion after heat treatment, there are surpluses；（4）Support fixture structure is simple, easy to assembly, low in cost, is easy to Implement, avoid due to heat-treatment distortion causes blade trailing edge gap overproof in addition due to deflection cause greatly with inner ring adhesion and The possibility scrapped.
Detailed description of the invention
Invention is further described in detail with reference to the accompanying drawings of the specification：
Fig. 1 is the assembling schematic diagram of one stage diverter of gas turbine of the present invention；
Fig. 2 is the partial schematic diagram of Fig. 1；
Fig. 3 is the partial enlarged view of A in Fig. 2 of the present invention；
Fig. 4 is the structural schematic diagram of support fixture of the present invention.
In figure：Inner ring 1, outer ring 2, blade 3, blade trailing edge 4, gap 5, support fixture 6, support ring 61, interconnecting piece 62 are recessed Slot 63, the first support frame 64, the second support frame 65, protrusion 66, jack 67.
Specific embodiment
Embodiment 1 as shown in figure 4, the present embodiment support fixture 6, including two semiorbicular support rings 61, support ring 61 middle inside protrusion setting interconnecting piece 62, interconnecting piece 62 are equipped with groove 63；Support fixture 6 further includes the first support frame 64 With the second support frame 65, one end of the first support frame 64 is equipped with protrusion 66, and the other end is equipped with jack 67, the second support frame 65 One end is again provided with protrusion 66, and the other end of the second support frame 65 is mating in the jack 67 of the first support frame 64, group The integral support component in bar shaped.
First support frame 64 when use, the second support frame 65 protrusion 66 respectively with the interconnecting piece 62 of two support rings 61 On groove 63 it is mating, the first support frame 64, the second support frame 65 by 67 grafting of jack be connected, by two support rings 61 A support fixture 6 is connected into, 2 inside of outer ring of one stage diverter of gas turbine is assemblied in close to 1 endface of inner ring, forms branch Support, reduce heat treatment and cooling procedure in outer ring 1 contraction, avoid because outer ring 2 effect of contraction blade trailing edge 4 and inner ring 1 it Between gap size.
A kind of one stage diverter assembly method of gas turbine, includes the following steps：
A. 20 blade 3 and 20 piece blade trailing edges 4 are fixedly linked, form blade assembly.
B. the blade profile hole on inner ring 1 and outer ring 2 is polished, the both ends of blade 3 are inserted into inner ring 1 and outer ring 2 accordingly respectively In the leaf basin in blade profile hole；At this time there are gap between blade trailing edge 4 and inner ring 1,20 groups of blade trailing edges 4 and inner ring 1 at this time are measured Between gap size.
C. it is packed into gasket in the gap 5 of inner ring 1 and blade trailing edge 4, blade 3 and inner ring 1 is welded and fixed.
D. blade 3 and outer ring 2 are welded and fixed；The gasket between blade trailing edge 4 and inner ring 1 is removed after the completion；It surveys Measure gap size between 20 groups of blade trailing edges 4 and inner ring 1 at this time.
E. support fixture 6 is installed close to 1 endface of inner ring in outer ring 2.
F. aging strengthening model is carried out in nitrogen protection atmosphere furnace, heat treatment temperature is 710 ± 10 DEG C, and soaking time 14 is small When, at rear taking-up support fixture 6, measure gap size between 20 groups of blade trailing edges 4 and inner ring 1 at this time.
The gasket of selection is 1Cr18Ni9Ti gasket, and intensity is high, and be easy to extend processing, cheap, the shape of gasket and Gap shape between blade trailing edge 4 and inner ring 1 matches.Consider the contraction distortion of heat treatment, selects the pad with a thickness of 0.6mm Piece, when welding, play a supportive role to the gap 5 between inner ring 1 and blade trailing edge 4, it is possible to prevente effectively from outer ring 2, inner ring 1 are being welded Contraction distortion when connecing influences the size in gap 5.
In step C, before blade 3 and inner ring 1 are welded and fixed, blade 3 and inner ring 1 are first subjected to tack welding It connects, then soldering test part and detects, blade 3 and inner ring 1 are welded again after part detection to be tested is qualified, it is ensured that welding is imitated Fruit.
In step D, before blade 3 and outer ring 2 are welded and fixed, blade 3 and outer ring 2 are first subjected to tack welding It connects, equally soldering test part and detects again, blade 3 and outer ring 2 are welded again after part detection to be tested is qualified, it is ensured that weld Effect.
In assembling process, before step B, step D, step F measure welding respectively, before heat treatment, 20 after heat treatment Locate the gap size between blade trailing edge 4 and inner ring 1, the data measured referring to table 1, be heat-treated rear blade trailing edge 4 and inner ring 1 it Between gap size be all in 0.33mm to the matching requirements between 0.43mm, meeting 0.3mm to 0.5mm, assembly qualified rate 100%, thoroughly solve the problems, such as that assembly qualified rate is low.
Gap size between 1 blade trailing edge of table and inner ring
Gap size between 1 blade trailing edge of table and inner ring
Serial number Weld anterior diastema/mm It is heat-treated anterior diastema/mm It is heat-treated post gap/mm
1 0.46 0.43 0.40
2 0.44 0.42 0.38
3 0.45 0.46 0.41
4 0.45 0.42 0.40
5 0.43 0.45 0.41
6 0.46 0.47 0.43
7 0.47 0.49 0.42
8 0.44 0.45 0.39
9 0.49 0.46 0.34
10 0.48 0.45 0.36
11 0.42 0.46 0.34
12 0.43 0.47 0.35
13 0.41 0.46 0.37
14 0.45 0.48 0.38
15 0.46 0.45 0.39
16 0.35 0.38 0.33
17 0.45 0.42 0.39
18 0.49 0.46 0.38
19 0.43 0.45 0.39
20 0.41 0.40 0.36
Obviously, the above embodiment is merely an example for clearly illustrating the present invention, and is not to implementation of the invention The restriction of mode.For those of ordinary skill in the art, can also make on the basis of the above description it is other not With the variation or variation of form.There is no necessity and possibility to exhaust all the enbodiments.And these belong to it is of the invention The obvious changes or variations that spirit is extended out are still in the protection scope of this invention.

Claims (5)

1. a kind of assembly method of one stage diverter of gas turbine, which is characterized in that include the following steps：
A. by blade（3）And blade trailing edge（4）It is fixedly linked, forms blade assembly；
B. inner ring is polished（1）And outer ring（2）On blade profile hole, by blade（3）Both ends be inserted into the inner ring respectively（1）And outer ring （2）In the leaf basin in corresponding blade profile hole；Blade trailing edge at this time（4）With inner ring（1）Between there are gaps；
C. in inner ring（1）With blade trailing edge（4）Gap（5）Interior loading gasket, by blade（3）With inner ring（1）Weld solid It is fixed；
D. by blade（3）With outer ring（2）It is welded and fixed；Blade trailing edge is removed after the completion（4）With inner ring（1）Between pad Piece；
E. in the outer ring（2）The internal close inner ring（1）Endface is installed by support fixture（6）；
F. aging strengthening model is carried out, takes out support fixture after the completion（6）, obtain one stage diverter of gas turbine and go forward side by side performing check.
2. nozzle ring assembly method according to claim 1, which is characterized in that the gasket in step C is 1Cr18Ni9Ti gasket, the gasket with a thickness of 0.4mm to 0.6mm.
3. a kind of support fixture of one stage diverter assembly method of gas turbine as claimed in claim 2, which is characterized in that Including：First support frame（64）, the second support frame（65）, concave surface is opposite when use and the symmetrically arranged semiorbicular support of a pair Ring（61）, first support frame（64）, the second support frame（65）The whole support component in bar shaped is formed after mating, it should The both ends of support component respectively with the pair of support ring（61）Middle inside it is mating, by the support ring（61）Connection At support fixture.
4. support fixture according to claim 3, which is characterized in that the support ring（61）Middle inside protrude setting Interconnecting piece（62）, the interconnecting piece（62）It is equipped with groove（63）.
5. support fixture according to claim 3, which is characterized in that first support frame（64）One end be equipped with protrusion Portion（66）, the other end is equipped with jack（67）, second support frame（65）One end be again provided with protrusion（66）, described second Support frame（65）The other end it is mating in first support frame（64）Jack in（67）, the protrusion（66）Grafting Cooperation is in the support ring（61）Interconnecting piece（62）Groove（63）It is interior.
CN201810924093.5A 2015-09-08 2015-09-08 The one stage diverter fixture of gas turbine of aero-engine Pending CN108817815A (en)

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CN201510567883.9A CN106493556B (en) 2015-09-08 2015-09-08 A kind of one stage diverter assembly method of gas turbine and support fixture
CN201810924093.5A CN108817815A (en) 2015-09-08 2015-09-08 The one stage diverter fixture of gas turbine of aero-engine

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CN201510567883.9A Active CN106493556B (en) 2015-09-08 2015-09-08 A kind of one stage diverter assembly method of gas turbine and support fixture
CN201810924093.5A Pending CN108817815A (en) 2015-09-08 2015-09-08 The one stage diverter fixture of gas turbine of aero-engine
CN201810924091.6A Pending CN109048217A (en) 2015-09-08 2015-09-08 One stage diverter of gas turbine of aero-engine
CN201810924707.XA Pending CN109079436A (en) 2015-09-08 2015-09-08 Blade trailing edge and lesser one stage diverter of gas turbine of ring gap

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CN201810924707.XA Pending CN109079436A (en) 2015-09-08 2015-09-08 Blade trailing edge and lesser one stage diverter of gas turbine of ring gap

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CN108032251B (en) * 2017-12-11 2020-03-24 中国航发南方工业有限公司 Turbine guider outer ring installation frock
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CN113894512B (en) * 2021-11-15 2024-03-01 中国航发贵州黎阳航空动力有限公司 Machining method of engine bow-shaped bracket assembly

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CN109048217A (en) 2018-12-21
CN109079436A (en) 2018-12-25
CN106493556A (en) 2017-03-15
CN106493556B (en) 2018-09-21

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