CN204312136U - The wheel disc seam position structure of gas turbine rotor and gas turbine rotor - Google Patents
The wheel disc seam position structure of gas turbine rotor and gas turbine rotor Download PDFInfo
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- CN204312136U CN204312136U CN201420721881.1U CN201420721881U CN204312136U CN 204312136 U CN204312136 U CN 204312136U CN 201420721881 U CN201420721881 U CN 201420721881U CN 204312136 U CN204312136 U CN 204312136U
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Abstract
The utility model relates to gas turbine rotor field, disclose a kind of wheel disc seam position structure of gas turbine rotor, two described wheel disc axially superpositions, an end face relative at two described wheel discs is provided with axial projection, other end is provided with axial notch, the internal diameter interference fit of described axial raised external diameter and axial notch; Described axial projection is provided with magnitude of interference and regulates breach; Described magnitude of interference regulates breach to be arranged on the circular breach on described axial raised axial end.Wheel disc seam position structure of the present utility model makes the wheel disc of rotor can adopt less magnitude of interference when assembling, reduce device extrusion stress, and be convenient to assembling, reduce the requirement to frock, closely cooperate when guaranteeing that rotor in working order simultaneously and do not loosen, ensure that the integrity of gas turbine rotor.Meanwhile, the utility model also provides a kind of gas turbine rotor.
Description
Technical field
The utility model relates to gas turbine rotor field, particularly relates to a kind of wheel disc seam position structure and gas turbine rotor of gas turbine rotor.
Background technique
Gas turbine rotor be included in pusher side of calming the anger section, turbine pusher side section and connect the jack shaft of two sections, two sections include multistage wheel disc, the end face relative engagement of adjacent two wheel discs of multistage wheel disc.Process axial projection at an end face of two adjacent wheel discs, its another relative end face processes axial notch, axial projection grafting enters axial notch and forms seam location fit.Axial projection coordinates with the installation of axial notch the requirement needing strict coaxality.
For realizing radial direction and axially locating requirement, the wheel discs at different levels of gas turbine rotor are when assembling, and seam location fit place adopts interference fit, and namely the internal diameter of axial raised external diameter and axial notch forms interference fit.Conventional gas turbine rotor does not get loose in order to adjacent wheel disc seam location fit place when ensureing work, usually given larger initial assembling magnitude of interference, in working order, due to the impact of centrifugal force and temperature, cooperation place can deform, and the magnitude of interference of cooperation place changes.Obviously, magnitude of interference is large, then adjacent fan-wheel radial fit is just tight, the stress of wheel disc interference yield is also just larger, affect wheel disc partial structurtes intensity, excessive magnitude of interference even may make the outer wall of the axial notch of cooperation ftracture, and the installation between adjacent wheel disc can be made comparatively difficult simultaneously.If magnitude of interference is too little, under working speed, coordinate interference face to loosen, affect rotor centering.In order to enable the cooperation between multistage wheel disc be positioned at zone of reasonableness, just need complete installation through regulating wheel wheel disc molded line repeatedly.In addition, the rotor mounting structure of prior art even can cause the durability of structure to reduce sometimes, needs use the material of high strength or thicken wheel disc thickness and even develop new assembly technology, there is the problem causing high cost.
Model utility content
(1) technical problem that will solve
The purpose of this utility model is to provide the wheel disc seam position structure of gas turbine rotor, improves the degree that closely cooperates between wheel disc, and provides gas turbine rotor.
(2) technological scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of wheel disc seam position structure of gas turbine rotor, two described wheel disc axially superpositions, an end face relative at two described wheel discs is provided with axial projection, other end is provided with axial notch, the internal diameter interference fit of described axial raised external diameter and axial notch; Described axial projection is provided with magnitude of interference and regulates breach; Described magnitude of interference regulates breach to be arranged on the circular breach on described axial raised axial end.
Wherein, described magnitude of interference regulates the axial depth of breach to be more than or equal to axial raised 1/2 length, and is less than the distance of described axial raised axial end and described wheel disc longitudinal center line; Described magnitude of interference regulates the radial dimension of breach to be greater than 1/6 of described axial raised external diameter and difference in internal diameters, and is less than 3/5 of described axial raised external diameter and difference in internal diameters.
Wherein, described axial projection is bulge loop, and described magnitude of interference regulates breach to be the circular breach excised along the aperture surface of described bulge loop and the position, axial end boundary of bulge loop.
Wherein, the cross section of described circular breach is rectangle.
Wherein, the cross section of described circular breach is class triangle, and described triangle slopes inwardly along the axial end of described bulge loop.
The utility model also provides a kind of gas turbine rotor, be included in the compressor rotor unit of pusher side of calming the anger, at the turbine rotor unit of turbine pusher side and the jack shaft for connecting two rotor units, described compressor rotor unit and turbine rotor unit include the wheel disc of multiple axle to superposition, an end face relative at adjacent two described wheel discs is provided with axial projection, other end is provided with axial notch, the internal diameter interference fit of described axial raised external diameter and axial notch; Described axial projection is provided with magnitude of interference and regulates breach; Described magnitude of interference regulates breach to be arranged on the circular breach on described axial raised axial end.
Wherein, the axial same position of multistage described wheel disc is provided with tie rod hole, and connects multistage described wheel disc by pull bar.
(3) beneficial effect
The wheel disc seam position structure of gas turbine rotor of the present utility model, be provided with magnitude of interference in the axial projection of seam position structure and regulate breach, thus make axial projection that radial change occur in rotor boosting velocity procedure, make to turn tighter and tighter between wheel disc, therefore, the wheel disc of rotor can adopt less magnitude of interference when assembling, reduce device extrusion stress, and be convenient to assembling, reduce the requirement to frock, closely cooperate when guaranteeing that rotor in working order simultaneously and do not loosen, ensure that the integrity of gas turbine rotor, reduce or avoid the adjacent wheel disc trace vibrating and may occur under long-term work to slide or relative displacement, the quality of improving product gas turbine and obtain good economic benefit.
Accompanying drawing explanation
Fig. 1 is gas turbine rotor structural representation of the present utility model;
Fig. 2 is the wheel disc seam position structure embodiment 1 sectional view (half of wheel disc is only shown) of gas turbine rotor of the present utility model;
Fig. 3 is the sectional view of wheel disc seam position structure embodiment 1 second level wheel disc of gas turbine rotor of the present utility model;
Fig. 4 is wheel disc seam position structure embodiment 2 sectional view of gas turbine rotor of the present utility model;
Fig. 5 is wheel disc seam position structure embodiment 2 sectional view of gas turbine rotor of the present utility model;
Fig. 6 is wheel disc seam position structure embodiment 3 sectional view of gas turbine rotor of the present utility model.
In figure, 1: gas compressor spindle nose; 2: gas compressor pull-rod nut; 3: compressor disk; 4: gas compressor moving blade; 5: gas compressor pull bar; 6: turbine wheel disc; 7: turbine rotor vane; 8: turbine pull bar; 9: turbine pull-rod nut; 10: turbine spindle nose; 20: center steering axis; 21: wheel disc seam position structure; 50: first order wheel disc; 60: second level wheel disc; 51: axial notch; 61: axial projection; 100: compressor rotor unit; 200: jack shaft; 300: turbine rotor unit; 600: wheel disc longitudinal center line; 601: protruding outer ring surface; 602: protruding axial end; 603: protruding inner ring surface; 605,605-1,605-2,605-3: magnitude of interference regulates breach.
Embodiment
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following instance for illustration of the utility model, but is not used for limiting scope of the present utility model.
Fig. 1 is the structural representation of gas turbine rotor, is included in the compressor rotor unit 100 of pusher side of calming the anger, jack shaft 200 and turbine rotor unit 300 3 part at turbine pusher side from front to back successively.Compressor rotor unit comprises gas compressor spindle nose 1, compressor disk 3 and is arranged on the gas compressor moving blade 4 of the circle circumferentially spaced on compressor disk 3, gas compressor pull bar 5 and gas compressor pull-rod nut 2.Gas compressor moving blade 4 is arranged on the outside of compressor disk 3, compressible air acting under the driving of compressor disk 3.Adjacent compressor disk 3 is axially stacking each other, and end face is positioned opposite, by gas compressor pull bar 5 and gas compressor nut 2 pretension, and is connected with gas compressor spindle nose 1, and form compressor rotor unit 100, compressor disk 3 can rotate around center steering axis 20.Turbine rotor unit 300 comprises turbine spindle nose 10, turbine wheel disc 6 and is arranged on the turbine rotor vane 7 of the circle circumferentially spaced on turbine wheel disc 6, turbine pull bar 8 and turbine nut 9.Turbine rotor vane 7 is arranged on the radial outside of turbine wheel disc 6, can make the interior merit that can be converted into turbine rotor unit 300 and rotate of high-temperature high-pressure fuel gas.Similar to compressor rotor unit 100, the axial card of turbine wheel disc 6 is provided with tie rod hole, by turbine pull bar 7 and turbine nut 9 stacking vertically, and to be connected with turbine spindle nose 10, turbine rotor unit 300 can be formed along axial stacks.Turbine rotor unit 300 is connected with compressor rotor unit 100 by intermediate connecting shaft 200, and the generator driving gas compressor and be connected with gas compressor, to produce electric energy.
Fig. 2 is the schematic diagram of the wheel disc seam position structure 21 of gas turbine rotor, and Fig. 3 is the structure sectional view of second level wheel disc 60.With reference to shown in Fig. 2 and Fig. 3, wheel disc seam position structure 21 represents the cooperating structure between any two adjacent wheel discs of the axial heap poststack of multistage wheel disc, in the present embodiment, wheel disc seam position structure 21 is applicable to the cooperating structure of the arbitrary neighborhood two stage turbine wheel disc 6 in the turbine rotor unit 300 shown in Fig. 1, or the cooperating structure of arbitrary neighborhood two stage compressor wheel disc 3 in compressor rotor unit 100.Wheel disc seam position structure 21 comprises first order wheel disc 50 and wheel disc 60 two wheel discs in the second level superpose vertically.First order wheel disc 50 and second level wheel disc 60 are compressor disk 3, turbine wheel disc 6 or other wheel discs known in the art in related domain.First order wheel disc 50 and second level wheel disc 60 can be solid wheel dish also can be hollow wheels dish.With reference to shown in Fig. 2, the right side of first order wheel disc 50 is relative with the left side of second level wheel disc 60, is provided with an axial notch 51 in first order wheel disc 50 right side, is provided with an axial projection 61 in second level wheel disc 60 left side.Axial projection 61 grafting enters in axial notch 51, for ensureing the coaxality of adjacent wheel disc, realize radial centering and location, axial projection 61 and axial notch 51 are relative to each other aimed at tangentially aliging radial, the inner ring surface 501 of axial notch 51 aligns with the outer ring surface 601 of axial projection 61, and the internal diameter of the external diameter of axial projection 61 and axial notch 51 forms interference fit.The axial end 602 of the axial projection 61 of second level wheel disc 60 is smooth.When wheel disc is hollow wheel disc, axial projection 61 is annulus, and the inner ring surface 603 of axial projection 61 is a smooth anchor ring.When wheel disc is solid wheel disc, there is not inner ring surface in axial projection 61.
With reference to shown in Fig. 2 and 3, axial projection 61 arranges magnitude of interference and regulates breach 605, magnitude of interference regulates breach 605 for being arranged on the circular breach on the axial end 602 of axial projection 61.Magnitude of interference regulates the axial depth of breach 605 to be more than or equal to axial raised 1/2 length, and is less than the axial end of axial projection 605 and the distance of wheel disc longitudinal center line 600.Such as magnitude of interference regulates the axial depth value of breach 605 to be axial raised 1/2,3/4 or 3/5.Magnitude of interference regulates the radial dimension of breach 605 to be greater than axial raised external diameter (diameter) and 1/6 of internal diameter (diameter) difference, and is less than axial raised external diameter (diameter) and 3/5 of internal diameter (diameter) difference.Such as magnitude of interference regulates the radial dimension value of breach 605 to be axial raised external diameter (diameter) and 1/5,1/4,2/5,1/3 or 1/2 of internal diameter (diameter) difference.Especially, when wheel disc is solid wheel disc, axial projection 61 does not have inner ring surface, and now, axial raised internal diameter is 0.Breach 605 is regulated by arranging magnitude of interference, when wheel disc rotates, axial displacement between first order wheel disc 50 and second level wheel disc 60 is constant, increase the radial displacement of axial projection 61, axial projection is made to press to axial notch 51, thus realize first order wheel disc 50 and the seam location fit of second level wheel disc 60, do not need just to use larger magnitude of interference when mounted, the required initial interference of wheel disc seam position structure 21 can be reduced.With reference to shown in Fig. 2 and 3, the axial projections 61 of the present embodiment is bulge loop, and magnitude of interference regulates breach 605 to be the circular breach excised along the aperture surface of bulge loop and the position, axial end boundary of bulge loop, and the cross section of this circular breach is class rectangular configuration.
In a preferred embodiment, magnitude of interference regulates the axial depth of breach 605 slightly larger than axial raised length, and as far as possible away from the distance of wheel disc longitudinal center line 600; Magnitude of interference regulates the radial dimension of breach 605 to equal axial raised external diameter (diameter) and 1/4 of internal diameter (diameter) difference.The advantage of this embodiment is to maximise the regulating action of breach design to magnitude of interference, minimizes again the weakening effect of this breach design to disc strength.
With reference to shown in Figure 4 and 5, the axial projection 61 of the present embodiment is bulge loop, magnitude of interference regulates breach 605-1 and magnitude of interference to regulate breach 605-2 to have a common boundary the circular breach that position excises along aperture surface 603 and the axial end 602 of bulge loop of bulge loop, the cross section structure triangular in shape of this circular breach, triangle slopes inwardly along the axial end of bulge loop.
With reference to shown in Fig. 6, the axial projection 61 of the present embodiment is boss, and magnitude of interference adjustment breach 605-3 is the circular breach of axial end 602 excision of vertically protruding 61, the rectangular structure of cross section of this circular breach.
By wheel disc seam position structure of the present utility model, be provided with magnitude of interference in the axial projection of seam position structure and regulate breach, thus make axial projection that radial change occur in rotor boosting velocity procedure, make to turn tighter and tighter between wheel disc, therefore, the wheel disc of rotor can adopt less magnitude of interference when assembling, reduce device extrusion stress, the molded line repeatedly adjusting wheel disc is not needed to install, improve simple installation, reduce the requirement to frock, closely cooperate when guaranteeing that rotor in working order simultaneously and do not loosen, ensure that the integrity of gas turbine rotor, reduce or avoid the adjacent wheel disc trace vibrating and may occur under long-term work to slide or relative displacement.Do not need to carry out particularization process to the material of wheel disc, promote the performance of the wheel disc that common material is made, quality and effect of gas turbine get a promotion, and obtain good economic benefit.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (7)
1. the wheel disc seam position structure of a gas turbine rotor, it is characterized in that, two described wheel discs axially superpositions, an end face relative at two described wheel discs is provided with axial projection, other end is provided with axial notch, the internal diameter interference fit of described axial raised external diameter and axial notch; Described axial projection is provided with magnitude of interference and regulates breach; Described magnitude of interference regulates breach to be arranged on the circular breach on described axial raised axial end.
2. the wheel disc seam position structure of gas turbine rotor as claimed in claim 1, it is characterized in that, described magnitude of interference regulates the axial depth of breach to be more than or equal to axial raised 1/2 length, and is less than the distance of described axial raised axial end and described wheel disc longitudinal center line; Described magnitude of interference regulates the radial dimension of breach to be greater than 1/6 of described axial raised external diameter and difference in internal diameters, and is less than 3/5 of described axial raised external diameter and difference in internal diameters.
3. the wheel disc seam position structure of gas turbine rotor as claimed in claim 2, it is characterized in that, described axial projection is bulge loop, and described magnitude of interference regulates breach to be the circular breach excised along the aperture surface of described bulge loop and the position, axial end boundary of bulge loop.
4. the wheel disc seam position structure of gas turbine rotor as claimed in claim 3, it is characterized in that, the cross section of described circular breach is rectangle.
5. the wheel disc seam position structure of gas turbine rotor as claimed in claim 3, it is characterized in that, the cross section of described circular breach is class triangle, and described triangle slopes inwardly along the axial end of described bulge loop.
6. a gas turbine rotor, it is characterized in that, be included in the compressor rotor unit of pusher side of calming the anger, at the turbine rotor unit of turbine pusher side and the jack shaft for connecting two rotor units, described compressor rotor unit and turbine rotor unit include the wheel disc of multiple axle to superposition, an end face relative at adjacent two described wheel discs is provided with axial projection, other end is provided with axial notch, the internal diameter interference fit of described axial raised external diameter and axial notch; Described axial projection is provided with magnitude of interference and regulates breach; Described magnitude of interference regulates breach to be arranged on the circular breach on described axial raised axial end.
7. gas turbine rotor as claimed in claim 6, it is characterized in that, the axial same position of multistage described wheel disc is provided with tie rod hole, and connects multistage described wheel disc by pull bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420721881.1U CN204312136U (en) | 2014-11-26 | 2014-11-26 | The wheel disc seam position structure of gas turbine rotor and gas turbine rotor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420721881.1U CN204312136U (en) | 2014-11-26 | 2014-11-26 | The wheel disc seam position structure of gas turbine rotor and gas turbine rotor |
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| CN204312136U true CN204312136U (en) | 2015-05-06 |
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| CN201420721881.1U Active CN204312136U (en) | 2014-11-26 | 2014-11-26 | The wheel disc seam position structure of gas turbine rotor and gas turbine rotor |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104533532A (en) * | 2014-11-26 | 2015-04-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wheel disc spigot locating structure of gas turbine rotor and gas turbine rotor |
| CN105386794A (en) * | 2015-12-10 | 2016-03-09 | 西安航天动力研究所 | Turbine disc rigidity self-reinforcement turbine structure |
| CN110821883A (en) * | 2019-12-04 | 2020-02-21 | 哈尔滨电气股份有限公司 | Modularized compressor rotor applied to heavy gas turbine |
| CN114109511A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Novel disk center connecting structure and double-spoke-plate turbine disk with same |
-
2014
- 2014-11-26 CN CN201420721881.1U patent/CN204312136U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104533532A (en) * | 2014-11-26 | 2015-04-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wheel disc spigot locating structure of gas turbine rotor and gas turbine rotor |
| CN104533532B (en) * | 2014-11-26 | 2017-01-11 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wheel disc spigot locating structure of gas turbine rotor and gas turbine rotor |
| CN105386794A (en) * | 2015-12-10 | 2016-03-09 | 西安航天动力研究所 | Turbine disc rigidity self-reinforcement turbine structure |
| CN110821883A (en) * | 2019-12-04 | 2020-02-21 | 哈尔滨电气股份有限公司 | Modularized compressor rotor applied to heavy gas turbine |
| CN114109511A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Novel disk center connecting structure and double-spoke-plate turbine disk with same |
| CN114109511B (en) * | 2021-11-12 | 2024-06-18 | 中国航发沈阳发动机研究所 | Novel disk core connection structure and double-radial-plate turbine disk with same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Wheel disc spigot locating structure of gas turbine rotor and gas turbine rotor Effective date of registration: 20161104 Granted publication date: 20150506 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150506 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |