CN101526013B - Device for fixing turbine blades - Google Patents
Device for fixing turbine blades Download PDFInfo
- Publication number
- CN101526013B CN101526013B CN200910008165.2A CN200910008165A CN101526013B CN 101526013 B CN101526013 B CN 101526013B CN 200910008165 A CN200910008165 A CN 200910008165A CN 101526013 B CN101526013 B CN 101526013B
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- Prior art keywords
- fixed element
- turbine
- flat horizontal
- special
- blade
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a device for fixing turbine blades on a turbine disk of a turbine, in particular a gas turbine, wherein an axial profiled groove (16) running at least approximately parallel to the turbine axis of rotation (R) is formed for a turbine blade (14) on the turbine disk (12), into which groove a blade root (18) of a turbine blade (14) having a cross section matching the profiled cross section of the profiled groove (16) is inserted, and wherein a fixing element (32) is formed for the turbine blade (14), with which element the blade root (18) of the turbine blade (14) inserted into the profiled groove (16) is fixed in the axial direction. According to the invention, the fixing element (32) is fixed by clamping on the turbine disk (12) and firmly tensions the blade root in the axial direction. The invention also relates to a fastening element for such a device.
Description
Technical field
The present invention relates to one turbine blade is fixed on to turbo machine, especially the device on the turbine disk of combustion gas turbine, wherein, for the Design Turbine Blade on the turbine disk with at least approximately parallel axial special-shaped slot of turbo machine running shaft, the turbine blade blade root matching with the profiled cross-section of special-shaped slot on cross section should insert in this special-shaped slot, and be provided with fixed element for turbine blade, with this fixed element by fixing the turbine blade blade root that inserts special-shaped slot in the axial direction.In addition, the invention still further relates to a kind of fixed element for this device, and with the turbo machine of this fixing device.
Background technique
German patent DE 10 2,004 036 389 A1 show a kind of start described form for turbine blade being fixed on to the device on the turbine disk of turbo machine.In this known device, on the turbine disk, design a kind of axial special-shaped slot for each turbine blade, the blade root with respective cross-section of turbine blade axially inserts this special-shaped slot.On the blade root of turbine blade, designed a groove, fixed element stretches in this groove, and is fixed in a groove of the turbine disk, thereby prevents that the blade root of turbine blade from moving axially in special-shaped slot.Groove on turbine blade blade root has different radius of curvature, plays the effect of avoiding fixed element to move in groove.
Summary of the invention
Task of the present invention is to improve the fixing device of the above form.
According to the present invention, this task is the device by having feature described in claim 1, realizes especially by this way, and fixed element is stuck in the turbine disk and fixes, and fixed element by fixing blade root in the axial direction.Claim 10 has been protected a kind of corresponding fixed element, and claim 14 has been protected a kind of corresponding turbo machine.Dependent claims relates to preferred embodiment.
In device according to the present invention, in order to ensure fixation, fixed element need only be stuck on turbine blade.Different from the technology that adopted before, so just do not need the fixed element between the tensioning turbine disk and blade root, thereby make relative movement and relativity power between the turbine disk and blade root can directly not affect again fixed element fixing on the turbine disk, thereby make fixing device more stable and simple.
According to the present invention, only the turbine disk must be furnished with corresponding module, to fixed element is stuck on the turbine disk.So simplified the production of turbo machine on the whole, because only have parts, namely the turbine disk must be equipped with extra module, and turbine blade remains unchanged and maybe can have simple appearance profile.
Fixed element is stuck on the turbine disk, be especially fixed on two axial directions, thereby the blade root that makes to be embedded in the turbine blade in special-shaped slot is fixed in the axial direction.In this way, guarantee that turbine blade is securely fixed in special-shaped slot on the one hand, compared with the technology that adopted before, the required technical measures of attachment of turbine blades have been greatly simplified on the other hand.
According to the present invention, preferably can fix multiple turbine blades, all turbine blades that preferably can fixed turbine machine.For this reason, in the time that enforcement is of the present invention, has designed one for each turbine blade and can be stuck on the turbine disk and the fixed element that the blade root of each turbine blade can be fixed vertically.But, similarly also two, three or more turbine blades can be fixed on the turbine disk jointly with a fixed element.
In order further to improve the reliable fixation degree of turbine blade blade root, suggestion is design fixed element like this, and blade root is not only axially fixed in special-shaped slot, and for fixing in the axial direction, blade root in special-shaped slot by pre-tensioner.
According to device of the present invention preferred embodiment, for fixed element being stuck on the flat horizontal surface of at least approximate radial extension of the turbine disk, a draw-in groove extending with one heart with running shaft of suggestion design.Manufacturing in the process of the turbine disk, just can make such draw-in groove in very simple mode, for example, by cutting such as turning.Meanwhile, the fixed element that such draw-in groove has been guaranteed to be stuck in wherein is extremely firmly fixed.In addition, fixed element can very freely be located in draw-in groove, so just can offset the tolerance variations producing in manufacture process in simple mode.
According to this embodiment expansion scheme example, suggestion designs one and extends radially outwardly on draw-in groove, and preferably through the first clamping flange of rounding processing, and one extend radially inwardly, preferably through the second clamping flange of rounding processing.The clamping flange of design, especially because adopted rounding processing, can be stuck in fixed element in draw-in groove on the one hand easily like this, clamps on the other hand flange due to radially inwardly or stretch out, and can after fixed element blocks, guarantee its fixation.
Draw-in groove, in the total height of radial direction, with external diameter or the nominal diameter of the turbine disk, is especially preferably roughly 1 with the external diameter of compressor impeller: 67-1: 60 ratio, is especially roughly 1: 63.From fixation, combination force size and degree angle easy for installation, this ratio is best compromise proposal.For example draw-in groove with the turbine disk of 732mm compressor impeller outer diameter can have the radially extension of 8.0-8.4mm, then be the first radius of 2.0-2.4mm and the second radius that is positioned at the 1.0-1.4mm on its opposite, thereby form the second clamping flange of rounding.This draw-in groove is about 11-12.2mm in total height in the radial direction, and the compressor impeller outer diameter of 732mm corresponding to 60-66.5 doubly.
In order to make the turbine blade blade root in special-shaped slot more firm in the axial direction, for the mode of execution of being furnished with draw-in groove, suggestion is so arranged draw-in groove with respect to special-shaped slot from radial direction: special-shaped slot is transitioned into draw-in groove at least partly, and the blade root that inserts the turbine blade of corresponding special-shaped slot stretches in draw-in groove.In this way, the fixed element being stuck in draw-in groove just can apply the relatively high power that axially fastens to the blade root of turbine blade, preferably very high axial pre tightening force, because the strong point of fixed element is located on the blade root near draw-in groove turbine blade around.
Especially for the present embodiment of being furnished with draw-in groove, suggestion is used cross section to be Z-shaped arcuate segment as fixed element, and this arcuate segment has two flat horizontal surfaces, they by one preferably at least approx the middle connecting plate rectangular with it be connected with each other.In order to play snap action, the longitudinal edge of fixed element and two flat horizontal surfaces successively blocks.Now, because fixed element is Z-shaped, not only make fixed element be stuck in draw-in groove securely, and the prestressing force of consequent fixed element can be extraly by the blade root of turbine blade in the axial direction pretension in special-shaped slot.
For the blade root of further the improving turbine blade power that axially fastens in special-shaped slot, also advise portion's section of the blade root of the turbine blade under inserting special-shaped slot state completely slightly to stretch out from special-shaped slot, protrude by an opening of constructing on fixed element, and be fixed in this opening in the time that fixed element is stuck on the turbine disk.In this way, not only make the blade root of turbine blade at axial restraint in one direction, and make it also be axially fixed in the opposite direction simultaneously.Thus, just substantially can not there is to unclamp because of carelessness the situation of turbine blade blade root, but still only need to use the simplest instrument just can install.
For blade root is fixed in opening, according in this form of implementation of device of the present invention, on fixed element, design lug, this lug stretches into opening, and engages with the additional locking slot forming on turbine blade blade root.Be substituted on fixed element the lug of design integratedly, also can design independently locking member of one, this locking member is inserted in the locking slot of portion's section of the opening that stretches out fixed element of blade root and is supported on the fixed element that is subject to prestressing force effect.
In order further to simplify the production of this device, suggestion design special-shaped slot like this extends it on the whole axial length of the turbine disk in addition.For turbine blade is axially fixed in special-shaped slot, be provided with separately a fixed element clamping with the turbine disk at the two ends of each special-shaped slot, the turbine blade blade root that inserts special-shaped slot is axially fixed in this case between two fixed elements.Just do not need to protrude in this case the lug in opening.
According to another aspect, the present invention relates to a kind of fixed element for apparatus of the present invention.This fixed element be designed to by two flat horizontal surfaces form, cross section is Z-shaped arcuate segment, two flat horizontal surfaces are at least approximately connected with each other with their rectangular middle connecting plates by one.Under gripping orientation, this fixed element is fixed in draw-in groove with an one flat horizontal surface, and its another flat horizontal surface leans against on the end face of the turbine blade blade root that inserts special-shaped slot.
In order to obtain high mechanical support power, especially prestressing force in when clamping, from the longitudinal direction of fixed element laterally, the middle connecting plate of fixed element bends to S shape.By the S shape shape of middle connecting plate, fixed element is easy in a longitudinal direction be depressed and is just bearing in draw-in groove securely after blocking in the time blocking.
The size of fixed element is design so preferably: fixed element longitudinal transversely two spacing of pointing between unidirectional planes of flat horizontal surface be equivalent at least approx fixed element be material thickness or wall thickness 3-5 doubly, be preferably equivalent to 4 times of fixed element material thickness.In the particularly preferred form of implementation of one, this form of implementation is designed to have the compressor impeller of external diameter 732mm, and the spacing between two planes is equivalent to 4.8mm, and the material thickness of fixed element is 1.2mm.For other compressor impeller outer diameter, preferably make the ratio of spacing or material thickness and external diameter substantially within the scope of aforementioned proportion.This is the best compromise proposal between production and installation cost and axially support power.
In order to support well turbine blade blade root, the size of fixed element is design so preferably: be transversely equivalent at least approx from the 0.5-0.7 of the length of the flat horizontal surface of the support turbine blade blade root of the longitudinal direction of fixed element doubly preferably 0.6 times in two spacing of pointing between unidirectional planes of flat horizontal surface the longitudinal of fixed element.If the external diameter of compressor impeller is 732mm, the spacing of two flat horizontal surfaces is preferably 4.8mm, and the length of flat horizontal surface is 8.0mm.For other compressor impeller outer diameter, the ratio that preferably makes spacing or length and external diameter is substantially within the scope in this ratio.
With respect to the length of flat horizontal surface that supports turbine blade blade root, the total length of fixed element preferably its 1.8-2.2 doubly, especially 1.875 times.If use the compressor impeller of above-mentioned external diameter 732mm, the length of fixed element is preferably about 15.0mm.For other compressor impeller outer diameter, the ratio that preferably makes total length or length and external diameter is substantially within the scope in aforementioned proportion, and the 46-52 that especially external diameter of the turbine disk is equivalent to fixed element total length substantially doubly, is especially essentially 48.8 times.
Brief description of the drawings
To utilize an embodiment and describe the present invention in detail with reference to accompanying drawing below.Brief Description Of Drawings is as follows:
Fig. 1 is the local perspective view that according to the present invention, turbine blade is fixed on to the device on the turbine disk;
Fig. 2 is the sectional view along section line A-A in Fig. 1, wherein shows the blade root of the turbine blade fixing with fixed element;
Fig. 3 is the partial view through the longitudinal section of the turbine disk, and wherein showing a draw-in groove according to the present invention is how in device shown in Fig. 1, to use;
Fig. 4 is the perspective view of fixed element, wherein shows how this fixed element use in device shown in Fig. 1;
Fig. 5 is the side view of fixed element;
Fig. 6 is the side cross-sectional view that a kind of deformation program of draw-in groove shown in Fig. 3 amplifies.。
Embodiment
In Fig. 1 and Fig. 2, show an embodiment who according to the present invention, turbine blade 14 is fixed on to the device 10 on the turbine disk 12 with the form of part perspective view and cross sectional view.For attachment of turbine blades 14, on the turbine disk 12, be provided with cross section and be special-shaped special-shaped slot 16, the trend of this special-shaped slot is at least approximate parallel with turbo machine running shaft R.In special-shaped slot 16, axially insert a blade root 18 of turbine blade 14, this blade root is radially inwardly forming on the end of layout under installment state at turbine blade 14.Make in known manner blade root 18 match at the axial transversely cross section of direction of insertion and the cross section of special-shaped slot 16, thereby turbine blade 12 is being coupled together securely with the turbine disk 14 in the radial direction.
In order to prevent that blade root 18 from unclamping in the axial direction from special-shaped slot 16, design according to device 10 of the present invention, explain in detail its each element by Fig. 3 and Fig. 4 below.
Fig. 3 is the sectional view of portion's section of the turbine disk 12.On the flat horizontal surface 20 of the turbine disk 12 on Fig. 3 the right, formed one with the draw-in groove 22 of the concentric extension of running shaft R.Draw-in groove 22 has roughly rectangular bottom land 24 of a bearing of trend and running shaft R.Bottom land 24 is that the flange 26 that extends radially outwardly and one are the second flange 28 gauges that extend radially inwardly by one, it is rounded that flange 26 is transitioned into the part of draw-in groove 22, the second flange 28 is same rounded the second, and forms the radius 30 of 2.2mm, is transitioned into the bottom land 24 of draw-in groove 22.With respect to the special-shaped slot 16 arranging equably from radial direction and running shaft R spacing, draw-in groove 22 is arranged in this wise, and the end of radially the most inwardly arranging of each special-shaped slot 16 is ended in draw-in groove 22 and roughly below the second flange 28.
Are fixed elements 32 of showing with perspective view form in Fig. 4 according to the second primary component of device 10 of the present invention, it is stuck on the draw-in groove 22 in Fig. 3, is described in detail below.The fixed element 32 made from steel plate is designed to cross section and is Z-shaped arcuate segment 34.Arcuate segment 34 is made up of two flat horizontal surfaces 36 and 38 that extend at least approaching the plane of arranging in parallel to each other, at least approaches rectangular middle connecting plate 40 they are coupled together by trend and these two flat horizontal surfaces.Between two flat horizontal surfaces 36 and 38, the changeover portion 42 and 44 that is transitioned into middle connecting plate 40 formed the arcuate segment (corresponding special-shaped center line) of radius 1.6mm, thereby given the elasticity that fixed element 32 is relevant to shape from cross section.The longitudinal edge mutually deviating from 46 and 48 of two flat horizontal surfaces 36 and 38 is through rounding processing, and the radius of its chamfering radius and draw-in groove 22 matches.
In addition, in the central design of fixed element 32 opening 50 that at least approaches rectangle, it is roughly from the middle part of the first flat horizontal surface 36 shown in Fig. 4 bottom, and the changeover portion 44 that extends to middle connecting plate 40 through middle connecting plate 40 enters into the second flat horizontal surface 38 shown in Fig. 4 top.Lug 64 starts to protrude in opening 50 from the opening lower edge 52 of the opening 50 that forms at the first flat horizontal surface 36, and this lug at least closely ends at middle connecting plate 40 from the first flat horizontal surface 36 on the height of changeover portion 42.
At longitudinal transversely distance a between the plane in two identical sensings of flat horizontal surface 36 and 38 of fixed element corresponding to the material thickness d of fixed element 32 4 times, the turbine disk that is 732mm for external diameter in an illustrated embodiment, material thickness d is 1.2mm (consulting Fig. 5).
Fix in order to ensure the reliable of fixed element 32 in draw-in groove 22,0.6 times of the length l 1 of the flat horizontal surface 36 that the distance a between the plane of longitudinal two identical sensings at flat horizontal surface 36 and 38 transversely of fixed element 32 supports corresponding to the blade root 18 to turbine blade 14 of the longitudinal direction from fixed element 32 at least approx, in described embodiment, length is 8.0mm.
In described embodiment, from its longitudinal direction, the total length l2 of fixed element 32 is equivalent to 1.875 times of length l 1 of the flat horizontal surface 36 of the blade root 18 of supporting turbine blade 14 and is 15.0mm.For its turbine disk external diameter, preferably correspondingly demarcate above-mentioned absolute dimension, the ratio of itself and turbine disk external diameter is consistent haply.
Describe the installation of turbine blade 14 on the turbine disk 12 below with reference to Fig. 1 and Fig. 2, when mounted, first turbine blade 14 has been inserted in to the special-shaped slot 16 arranging on the turbine disk 12 by its blade root 18.Then with fixed element 32, each turbine blade 14 is fixed as shown in Figure 4.
For this object, fixed element 32 hangs over the longitudinal edge 46 of the first flat horizontal surface 36 on the first flange 26 of draw-in groove 22, lug 54 hangs on locking slot 56 simultaneously, and this locking slot is that the downside of a section stretching out from special-shaped slot 16 the blade root 18 of turbine blade 14 forms.
Then fixed element 32 is pressed to the turbine disk 12 towards axial direction, now the changeover portion 42 of the middle connecting plate 40 from the first flat horizontal surface 36 to fixed element 32 is stuck in the second flange 28 of draw-in groove 22.The radius 30 of the radius of changeover portion 42 and the second flange 28 matches, thereby these two flanges are engaged or clamping (consulting Fig. 2) mutually reliably.In this clamping process, blade root 18 moves to its final mounting point in special-shaped slot 16, and now blade root 18 can, under the effect of axial prestress, be maintained by the second flat horizontal surface 38 of the fixed element of clamping in draw-in groove 22.But similarly can not have prestressed ground by the second flat horizontal surface 38, blade root 18 only to be locked vertically yet and be not arranged in groove 16 at this point with stressing.
Meanwhile, blade root 18 is remained on predetermined axial position by the lug 54 of the fixed element 32 in engagement with the locking slot 56 of blade root 18.
Fig. 6 shown a draw-in groove slightly changing 22 ', difference is only compared with the draw-in groove 22 shown in Fig. 3, the trend of the first flange 26 at right angles or have a sharp rib.In this way, guaranteed fixed element 32 draw-in groove 22 ' in more firm.Draw-in groove 22 ' size corresponding to the size of draw-in groove 22 shown in Fig. 3, and match with the size of fixed element 32, the size shown in Fig. 6 just can be directly used in the draw-in groove 22 shown in Fig. 3 like this.
Therefore, approach the draw-in groove 22 of flange 26 ' width b larger than the material thickness d of fixed element 32, taking in the embodiment shown in zoomed-in view as 1.3mm.The radial depth t of the groove parallel with the flat horizontal surface of the turbine disk 14 is 2.0mm.Draw-in groove 22 ' one section of flat horizontal surface 36 that leans against fixed element 32 on, the radial length l3 of this section is 8.2mm.Two radius Rs 1 on the second flange 28 are consistent with the radius of middle connecting plate 40 with R2, and larger radius R 1 is 2.2mm, and less radius R 2 is 1.2mm.For the inconsistent turbine disk of the 732mm in external diameter and the present embodiment, also preferably correspondingly demarcate above-mentioned several or whole absolute dimension, the ratio of itself and turbine disk external diameter is consistent haply.
Utilize according to device 10 of the present invention, can with very simple and cleverly mode turbine blade 14 is axially fixed on the turbine disk 12.In this device 10, do not need groove with high costs, moulding is special, as described in the background art.
reference numerals list
10 devices
12 turbine disks
14 turbine blades
16 special-shaped slots
The blade root of 18 turbine blades
20 flat horizontal surfaces
R running shaft
22 draw-in grooves
24 bottom lands
26 first flanges
28 second flanges
30 radiuses
32 fixed elements
34 arcuate segments
36 flat horizontal surfaces
38 flat horizontal surfaces
40 middle connecting plates
42 changeover portions
44 changeover portions
46 longitudinal edges
48 longitudinal edges
50 openings
52 opening lower edges
54 lugs
56 fixed grooves
Spacing between a flat horizontal surface 36 and 38
D material thickness
The length of l1 flat horizontal surface 36
The total length of l2 fixed element
T draw-in groove 22 ' radial depth
B draw-in groove 22 ' width
L3 draw-in groove 22 ' radial length
Larger radius on R1 flange 28
Less radius on R2 flange 28
Claims (19)
1. one kind for being fixed on turbine blade (14) in the device on the turbine disk (12) of turbo machine, wherein, on the turbine disk (12), be provided with the approximate axial special-shaped slot (16) extending in parallel of running shaft with turbo machine for turbine blade (14), in this special-shaped slot, be inserted in turbine blade (14) blade root (18) matching with the profiled cross-section of special-shaped slot (16) on cross section, with be provided with fixed element (32) for turbine blade (14), the blade root (18) that utilizes this fixed element to make to insert the turbine blade (14) in special-shaped slot (16) locks in the axial direction, it is characterized in that: by being stuck in, the turbine disk (12) is upper to be fixed and blade root (18) is axially locked fixed element (32), wherein, in order to block fixed element (32), on the flat horizontal surface of the turbine disk (12), be provided with the draw-in groove (22) with the concentric distribution of running shaft (R), draw-in groove (22) carrys out read fortune from radial direction and arranges in this wise for special-shaped slot, make special-shaped slot (16) be transitioned at least in part draw-in groove (22), thereby turbine blade (14) blade root (18) that makes to insert special-shaped slot (16) protrudes in draw-in groove (22).
2. device as claimed in claim 1, is characterized in that, fixed element (32) is pre-tensioner in special-shaped slot (16) vertically by blade root (18) in order to lock in the axial direction.
3. device as claimed in claim 1, is characterized in that, draw-in groove (22) is limited by a first clamping flange (26) extending radially outwardly and/or a second clamping flange (28) extending radially inwardly.
4. device as claimed in claim 1, it is characterized in that, fixed element (32) is designed to cross section and is arcuate segment (34) Z-shaped, that be made up of two flat horizontal surfaces (36,38), these two flat horizontal surfaces are connected with each other with trend and their approximate rectangular middle connecting plates (40), it is inner that fixed element (32) remains on draw-in groove (22) by an one flat horizontal surface (36) under gripping orientation, and its another flat horizontal surface (38) abuts in the end face of turbine blade (14) blade root (18) that inserts special-shaped slot (16).
5. device as claimed in claim 3, it is characterized in that, fixed element (32) is designed to cross section and is arcuate segment (34) Z-shaped, that be made up of two flat horizontal surfaces (36,38), these two flat horizontal surfaces are connected with each other with trend and their approximate rectangular middle connecting plates (40), it is inner that fixed element (32) remains on draw-in groove (22) by an one flat horizontal surface (36) under gripping orientation, and its another flat horizontal surface (38) abuts in the end face of turbine blade (14) blade root (18) that inserts special-shaped slot (16).
6. the device as described in any one in claim 1 to 5, it is characterized in that, portion's section of turbine blade (14) blade root (18) is stretched out a little under the state that inserts special-shaped slot (16) completely from special-shaped slot (16), and described portion section is protruded and is locked in this opening in the time that fixed element (32) is stuck on the turbine disk (12) by the opening (50) of constructing on fixed element.
7. device as claimed in claim 6, it is characterized in that, for blade root (18) is locked in opening (50), one protrudes in opening (50) at the upper lug (54) arranging of fixed element (32), and this lug engages with the locking slot (56) of the upper structure of a blade root in turbine blade (14) (18).
8. the device as described in any one in claim 1 to 5, it is characterized in that, special-shaped slot (16) extends on the whole axial length of the turbine disk (12), and a fixed element (32) clamping with the turbine disk (12) is set separately at the two ends of each special-shaped slot (16), and turbine blade (14) blade root (18) that wherein inserts special-shaped slot (16) is axially locked between two fixed elements (32).
9. for the fixed element of the device as described in above-mentioned any one claim, it is characterized in that, fixed element (32) is designed to cross section and is Z-shaped, by two flat horizontal surfaces (36, 38) arcuate segment (34) forming, these two flat horizontal surfaces are used with they approximate at right angles middle connecting plates (40) of trend and are connected with each other, it is inner that fixed element (32) remains on draw-in groove (22) with an one flat horizontal surface (36) under gripping orientation, and its another flat horizontal surface (38) abuts on the end face of blade root (18) of the turbine blade (14) that inserts special-shaped slot (16).
10. fixed element as claimed in claim 9, is characterized in that, from fixed element transversely, middle connecting plate (40) bends to S shape.
11. fixed elements as claimed in claim 9, it is characterized in that, in the transversely distance (a) between the plane in two identical sensings of flat horizontal surface (36,38) of fixed element haply corresponding to the 3-5 of the material thickness (d) of fixed element (32) doubly, and/or haply corresponding to support turbine blade (14) blade root (18) flat horizontal surface (36) from the 0.5-0.7 of the vertical length looking up (L1) of fixed element (32) doubly.
12. fixed elements as claimed in claim 10, it is characterized in that, in the transversely distance (a) between the plane in two identical sensings of flat horizontal surface (36,38) of fixed element haply corresponding to the 3-5 of the material thickness (d) of fixed element (32) doubly, and/or haply corresponding to support turbine blade (14) blade root (18) flat horizontal surface (36) from the 0.5-0.7 of the vertical length looking up (L1) of fixed element (32) doubly.
13. fixed elements as claimed in claim 11, is characterized in that, described distance (a) is haply corresponding to 4 times of described material thickness (d), and/or are 0.6 times of described length (L1) haply.
14. fixed elements as described in any one in claim 9 to 13, it is characterized in that, the total length (L2) of fixed element (32) from its longitudinally see haply corresponding to support turbine blade (14) blade root (18) flat horizontal surface (36) from the 1.8-2.2 of the length of longitudinally seeing (L1) of fixed element (32) doubly, and/or the external diameter of the turbine disk is haply corresponding to the 46-52 of fixed element (32) total length (L2) longitudinally from it doubly.
15. fixed elements as claimed in claim 14, it is characterized in that, the total length (L2) of described fixed element (32) is 1.875 times of length (L1) of described flat horizontal surface (36) haply, and/or the external diameter of the turbine disk is 48.8 times of total length (L2) of described fixed element (32) haply.
16. 1 kinds of turbo machines, with the turbine disk (12) and fixing turbine blade (14) in the above, it is characterized in that having as described in above-mentioned any one claim for turbine blade (14) being fixed on to the device on the turbine disk (12) of turbo machine.
17. turbine disks for turbo machine as claimed in claim 16, is characterized in that, described turbo machine is combustion gas turbine.
18. turbine disks for turbo machine as claimed in claim 16, is characterized in that having a kind of draw-in groove (22), and the external diameter of the turbine disk is 60-67 times in total height in the radial direction corresponding to draw-in groove (22) haply.
19. turbine disks as claimed in claim 18, is characterized in that, the external diameter of the described turbine disk is draw-in groove (22) 63 times of total height in the radial direction haply.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102008013118.0 | 2008-03-07 | ||
| DE102008013118.0A DE102008013118B4 (en) | 2008-03-07 | 2008-03-07 | Arrangement for fastening turbine blades |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101526013A CN101526013A (en) | 2009-09-09 |
| CN101526013B true CN101526013B (en) | 2014-06-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910008165.2A Expired - Fee Related CN101526013B (en) | 2008-03-07 | 2009-03-09 | Device for fixing turbine blades |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JP5226561B2 (en) |
| KR (1) | KR101433966B1 (en) |
| CN (1) | CN101526013B (en) |
| CH (1) | CH698644B1 (en) |
| DE (1) | DE102008013118B4 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2386721A1 (en) * | 2010-05-14 | 2011-11-16 | Siemens Aktiengesellschaft | Fastening assembly for blades of axial fluid flow turbo machines and procedure for producing the same |
| US8753090B2 (en) * | 2010-11-24 | 2014-06-17 | Rolls-Royce Corporation | Bladed disk assembly |
| US9068465B2 (en) * | 2012-04-30 | 2015-06-30 | General Electric Company | Turbine assembly |
| CN105065065A (en) * | 2015-08-07 | 2015-11-18 | 山东青能动力股份有限公司 | Fir type blade root moving blade locking device and assembly process thereof |
| EP3581765A1 (en) * | 2018-06-11 | 2019-12-18 | Siemens Aktiengesellschaft | Rotor having rotor blades attached axially to the rotor disc |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1524160A (en) * | 2001-07-03 | 2004-08-25 | Abb涡轮***有限公司 | Securing system for the rotor blades of axial flow turbo engines |
| CN1656303A (en) * | 2002-05-24 | 2005-08-17 | Abb涡轮***有限公司 | Axial securing means for impeller blades |
| CN101160452A (en) * | 2005-03-24 | 2008-04-09 | 西门子迪马格德拉瓦尔涡轮机器公司 | Locking arrangement for radial entry turbine blades |
| CN101258305A (en) * | 2005-09-07 | 2008-09-03 | 西门子公司 | Arrangement for axially securing rotating blades in a rotor and use |
| CN101529052A (en) * | 2006-10-26 | 2009-09-09 | 西门子公司 | Turbine blade assembly |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2761648A (en) * | 1951-09-18 | 1956-09-04 | A V Roe Canada Ltd | Rotor blade locking device |
| DE1051286B (en) * | 1958-06-02 | 1959-02-26 | Her Majesty The Queen In The R | Fuse for a blade held in an axial groove of a centrifugal machine |
| US3656865A (en) | 1970-07-21 | 1972-04-18 | Gen Motors Corp | Rotor blade retainer |
| FR2695433B1 (en) | 1992-09-09 | 1994-10-21 | Snecma | Annular seal placed at an axial end of a rotor and covering blade pinouts. |
| GB9517369D0 (en) * | 1995-08-24 | 1995-10-25 | Rolls Royce Plc | Bladed rotor |
| FR2868808B1 (en) | 2004-04-09 | 2008-08-29 | Snecma Moteurs Sa | DEVICE FOR THE AXIAL RETENTION OF AUBES ON A ROTOR DISC OF A TURBOMACHINE |
| DE102004036389B4 (en) | 2004-07-27 | 2013-04-25 | Rolls-Royce Deutschland Ltd & Co Kg | Turbine blade root with multiple radius groove for axial blade attachment |
| EP1643082A1 (en) * | 2004-09-30 | 2006-04-05 | Siemens Aktiengesellschaft | Turbine blade retention system |
| DE102005035901A1 (en) * | 2005-07-30 | 2007-02-01 | Mtu Aero Engines Gmbh | Rotor blades` position securing unit for gas turbine, has plate-like base body having recess formed between its two end sections, where recess defines middle section of body and sections have contact surfaces running parallel to each other |
| US8128371B2 (en) * | 2007-02-15 | 2012-03-06 | General Electric Company | Method and apparatus to facilitate increasing turbine rotor efficiency |
-
2008
- 2008-03-07 DE DE102008013118.0A patent/DE102008013118B4/en not_active Withdrawn - After Issue
- 2008-12-08 CH CH01918/08A patent/CH698644B1/en not_active IP Right Cessation
-
2009
- 2009-01-23 KR KR1020090006029A patent/KR101433966B1/en not_active IP Right Cessation
- 2009-03-06 JP JP2009053835A patent/JP5226561B2/en not_active Expired - Fee Related
- 2009-03-09 CN CN200910008165.2A patent/CN101526013B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1524160A (en) * | 2001-07-03 | 2004-08-25 | Abb涡轮***有限公司 | Securing system for the rotor blades of axial flow turbo engines |
| CN1656303A (en) * | 2002-05-24 | 2005-08-17 | Abb涡轮***有限公司 | Axial securing means for impeller blades |
| CN101160452A (en) * | 2005-03-24 | 2008-04-09 | 西门子迪马格德拉瓦尔涡轮机器公司 | Locking arrangement for radial entry turbine blades |
| CN101258305A (en) * | 2005-09-07 | 2008-09-03 | 西门子公司 | Arrangement for axially securing rotating blades in a rotor and use |
| CN101529052A (en) * | 2006-10-26 | 2009-09-09 | 西门子公司 | Turbine blade assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102008013118B4 (en) | 2014-03-27 |
| DE102008013118A1 (en) | 2009-09-10 |
| CN101526013A (en) | 2009-09-09 |
| KR20090096311A (en) | 2009-09-10 |
| JP2009216096A (en) | 2009-09-24 |
| CH698644A2 (en) | 2009-09-15 |
| JP5226561B2 (en) | 2013-07-03 |
| CH698644B1 (en) | 2013-02-15 |
| KR101433966B1 (en) | 2014-08-25 |
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