CN1130713A - Bladed rotor - Google Patents
Bladed rotor Download PDFInfo
- Publication number
- CN1130713A CN1130713A CN95118856A CN95118856A CN1130713A CN 1130713 A CN1130713 A CN 1130713A CN 95118856 A CN95118856 A CN 95118856A CN 95118856 A CN95118856 A CN 95118856A CN 1130713 A CN1130713 A CN 1130713A
- Authority
- CN
- China
- Prior art keywords
- blade
- rotor
- pin
- hole
- groove
- 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
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Classifications
-
- 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
- F01D5/326—Locking of axial insertion type blades by other means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2200/00—Mathematical features
- F05D2200/10—Basic functions
- F05D2200/11—Sum
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The blade foot has an axial projection extending it in the groove direction (2). The bolt (6) is arranged within the axial projection. In the axial projection, a hole for dismantling the running blades (5) out of the blade grooves of the rotor is arranged. The spring force of the spring-type component (7) is at least as great as the sum of the friction of the bolt in the arbitrarily formed holes in the blade foot of the running blade and in the rotor (1), as well as the weight of the bolt.
Description
The present invention relates to a kind of vaned rotor of installation of turbo machine, at this, the blade root of turbine blade is fixed on the basic in the blade groove that axially stretches of rotor.
The vaned rotor of this installation is known.The blade that is fixed in the axial groove is fixed at its axial position.For this reason, be fixing final stage turbine blade group, a revolution T-slot is set on the bottom land height of axial groove in wheel rim especially.The formation of this T-slot and common rotary vane groove are similar, just turn 90 degrees in the wheel rim inward turning.With regard to each turbine blade group, T-slot is configured to arc and axial groove that tilt in addition.By the position of this T-slot on the bottom land height of blade groove, this T-slot is through blade root.By the opening of T-slot, can inject L shaped, with the corresponding arch-shaped elements of rotor circumference.T shape of the complementary one-tenth of the L shaped element that per two quilts advance side by side, and fill up T-slot fully.Said L shaped element is segmentation on circumference.Each section is wider than the blade root that common mode is provided with at least and covered about three blade roots or groove.After being encased in blade in the rotor, the piecewise is injected L shaped element in the T-slot successively.Thin L shaped element is used as closure member, can inject them together by opening.Embed a wedge as closure member between these two elements, this wedge is fixed in addition.
This fixed form is very time-consuming in the installation of turbine blade and possible unloading process.Jagged appearance in the manufacture process of this external groove, the removal of burr also are very complicated, and because this mode needs high energy consumption, have therefore caused corresponding expensive.
Task of the present invention is, make when beginning the vaned epitrochanterian sharf of described the sort of installation to safety element manufacture be easier to and cost lower.
According to the present invention, this task realizes by this way, be that each turbine blade axially is fixed in the blade groove by a movable pin at least, said pin can be settled by an elastic element with rebounding, and said pin connects together blade root and blade groove.
In addition, advantage of the present invention can be seen therein, promptly can load onto blade easily or pull down by movable pin.
In the accompanying drawings, by the rotor of a turbo machine one embodiment of the present of invention have been described.
Wherein:
Fig. 1 is one vaned drum cross section of rotor sectional view is installed;
Fig. 2 is the longitudinal section of II along the line among Fig. 1.
For understanding the present invention, shown just major part.
According to Fig. 1, rotor 1 is equipped with turbine blade 5.This turbine blade 5 is made of a blade 4 and a blade root 3 of only partly drawing.The blade root 3 of this turbine blade is inserted into basic in the blade groove 2 of longitudinally extending rotor 1.This blade root 3 is made of with the Chinese fir form a plurality of sawtooth 11.Blade groove 2 in the drum rotor 1 is made of respective saw teeth 20 equally.If rotor rotation, just turbine blade 5 radially outwards quicken, at this moment they are held by drum rotor 1 by the fir tree means of fixation.The axial relief element that is made of a pin 6 and spring 7 is positioned in the hole 9 in the axial projection 12 of hole 8 in the rotor root basal plane and blade root 3.Hole 8 and hole 9 are made of blind hole at this.
According to Fig. 2, hole 9 is in the axial projection 12 of blade root 3 fully.Therefore hole 9 is located at outside that zone of the blade root 3 that is loaded when rotor 1 rotates.Thus, blade root can't weaken because of hole 9.On pin 6, another one hole 13 is set also in axial projection 12.Yet the diameter in hole 13 is less than the diameter in hole 9.
When mounting turbine blades 5, spring 7 is inserted in the hole 8, then in the pin 6 also patchhole 8.Can press downward to distance so long in the hole 8 to pin 6, so that it no longer stretches out the bottom land of blade groove 2.At this moment be inserted into blade 5 in the blade groove 2 and push away the pin 6 of excessive rolling, till hole 9 is positioned at 8 tops, hole.In this position, spring 7 is upwards oppressed pin 6, makes it enter into hole 9, and therefore turbine blade is axially fixed.Certainly, spring 7 must so be provided with, so that the size of spring force is at least the frictional force of pin 6 in hole 8 and 9 and the summation of pin weight.In dismounting during turbine blade 5, for example can by one be inserted in the hole 13 at this probe of not depicting, to lower compression pin 6.The safty device of turbine blade are opened and can be axially pushed out for 2 li from blade groove whereby.
Obviously, the present invention is not limited to shown and described embodiment.The form of the composition of said axial groove is arbitrarily, for example can use axial groove arc or rhombus in other words.The formation in said pin and affiliated hole thereof also is arbitrarily.Importantly the setting of the mobility of pin in the hole, the pin relevant with axial force and turbine blade are axial fixing.Hole 9 in the blade root can also constitute with the groove form.At least the part that extend into the pin in the hole 9 for example can be arranged to have the plane, and these planes and stress direction are rectangular.So that these planes increase, power is transmitted by these planes.As spring, can use any elastic element.
1 rotor
Blade groove in 2 rotors
3 blade roots
4 blades
5 turbo blades
6 pins
7 springs
Hole in 8 rotors
Hole in 9 blade roots
11 zigzag fashion blade roots
12 axial protruding blade roots
13 removal holes
20 zigzag fashion longitudinal grooves
Claims (4)
1. the vaned rotor of the installation of turbo machine (1), wherein, the blade root (3) of turbine blade (5) is fixed on the basic in the blade groove (2) that axially stretches of rotor,
It is characterized in that:
Each turbine blade (5) axially is fixed in the blade groove by a movable pin (6) at least, and said pin can be settled by an elastic element (7) with rebounding, and said pin connects together blade root (3) and blade groove (2).
2. according to the vaned rotor of the installation of claim 1, it is characterized in that:
Said blade root (3) has an axial projection (12) the last lengthening of groove direction (2) blade root, and said pin (6) is set in the axial projection (12).
3. according to the vaned rotor of the installation of claim 1, it is characterized in that:
Being provided with one in axial projection (12) is used for turbine blade (5) from hole that the blade groove of rotor (2) disassembles.
4. according to the vaned rotor of the installation of claim 1, it is characterized in that:
The size of the spring force of said elastic element (7) is at least pin (6) and is being the blade root in turbine blade (5) (3) and the frictional force in the hole (8,9) in the rotor (1) and the summation of pin weight that constitutes arbitrarily substantially.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE4441233A DE4441233A1 (en) | 1994-11-19 | 1994-11-19 | Bladed rotor |
| DEP4441233.9 | 1994-11-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1130713A true CN1130713A (en) | 1996-09-11 |
Family
ID=6533664
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN95118856A Pending CN1130713A (en) | 1994-11-19 | 1995-11-19 | Bladed rotor |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP0712995A1 (en) |
| JP (1) | JPH08210103A (en) |
| CN (1) | CN1130713A (en) |
| DE (1) | DE4441233A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101096914B (en) * | 2006-06-29 | 2010-08-11 | 斯奈克玛 | Turbomachine rotor and turbomachine comprising such a rotor |
| CN102444479A (en) * | 2010-10-12 | 2012-05-09 | 通用电气公司 | Axial retention device for turbine system |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6761538B2 (en) * | 2002-10-31 | 2004-07-13 | General Electric Company | Continual radial loading device for steam turbine reaction type buckets and related method |
| DE102005024932A1 (en) | 2005-05-31 | 2006-12-07 | Rolls-Royce Deutschland Ltd & Co Kg | Turbinenschaufelaxialsperre |
| EP1924757A1 (en) * | 2005-09-15 | 2008-05-28 | Alstom Technology Ltd | Cover strip comprising a detachable anchoring for a row of blades of a turbomachine |
| WO2007031383A1 (en) * | 2005-09-15 | 2007-03-22 | Alstom Technology Ltd | Blade of a turbomachine having detachable anchoring for a separate cover plate |
| EP1764479A1 (en) * | 2005-09-15 | 2007-03-21 | ALSTOM Technology Ltd | Coupled shroud plates for a row of blades of a turbomachine |
| EP1860280A1 (en) * | 2006-04-07 | 2007-11-28 | Siemens Aktiengesellschaft | Locking device of a turbine blade with a locking element |
| EP2299060A1 (en) * | 2009-09-17 | 2011-03-23 | Siemens Aktiengesellschaft | Blade fixation with locking device for turbine blades |
| JP5692994B2 (en) * | 2009-12-08 | 2015-04-01 | 三菱重工業株式会社 | Rotor blade fixing structure, rotating machine having the same, and rotor blade attaching / detaching method |
| US8992180B2 (en) * | 2011-08-24 | 2015-03-31 | General Electric Company | Replaceable staking insert assembly and method |
| GB201417705D0 (en) | 2014-10-07 | 2014-11-19 | Rolls Royce Plc | Locking member |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2846183A (en) * | 1952-07-18 | 1958-08-05 | William C Morgan | Retaining devices for turbine blades |
| US2953348A (en) * | 1952-12-30 | 1960-09-20 | Gen Motors Corp | Blade fastenings |
| US2847187A (en) * | 1955-01-21 | 1958-08-12 | United Aircraft Corp | Blade locking means |
| CH572155A5 (en) * | 1974-05-27 | 1976-01-30 | Bbc Sulzer Turbomaschinen | |
| DE2850941A1 (en) * | 1978-11-24 | 1980-06-12 | Motoren Turbinen Union | Gas turbine rotor ceramic blade fixture arrangement - has indentation at slot base in rotor body for location of small weight with spring retention |
| DE3341871A1 (en) * | 1983-11-19 | 1985-05-30 | Brown, Boveri & Cie Ag, 6800 Mannheim | Axial compressor |
-
1994
- 1994-11-19 DE DE4441233A patent/DE4441233A1/en not_active Withdrawn
-
1995
- 1995-10-30 EP EP95810673A patent/EP0712995A1/en active Pending
- 1995-11-15 JP JP7297078A patent/JPH08210103A/en active Pending
- 1995-11-19 CN CN95118856A patent/CN1130713A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101096914B (en) * | 2006-06-29 | 2010-08-11 | 斯奈克玛 | Turbomachine rotor and turbomachine comprising such a rotor |
| CN102444479A (en) * | 2010-10-12 | 2012-05-09 | 通用电气公司 | Axial retention device for turbine system |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH08210103A (en) | 1996-08-20 |
| DE4441233A1 (en) | 1996-05-23 |
| EP0712995A1 (en) | 1996-05-22 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C06 | Publication | ||
| PB01 | Publication | ||
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |