CN1936276A - Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method - Google Patents
Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method Download PDFInfo
- Publication number
- CN1936276A CN1936276A CNA2006101395352A CN200610139535A CN1936276A CN 1936276 A CN1936276 A CN 1936276A CN A2006101395352 A CNA2006101395352 A CN A2006101395352A CN 200610139535 A CN200610139535 A CN 200610139535A CN 1936276 A CN1936276 A CN 1936276A
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- China
- Prior art keywords
- mentioned
- impeller
- blank
- integral wheel
- processed
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- 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.)
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
-
- 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
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Integrated nozzle and bucket wheels (10, 44) for turbine stator and rotor components, respectively, include a three hundred sixty degree wheel formed from a single piece of stock material. The nozzle wheels (10) include radially inner portions formed to include a plurality of airfoils (16), while the bucket wheels are each formed to include a plurality of buckets (54). The nozzle and bucket wheels may be split into plural arcuate segments.
Description
The present invention be on September 7th, 2005 submit applications be numbered No.11/219,667 title is the part continuation application of the patent application of " the integrated nozzle dish and the correlation technique of reaction-type steamturbine static part ".
Invention field
The present invention relates generally to the steamturbine configuration, relates in particular to the integrated nozzle and the impeller configuration of reaction-type steamturbine.
Background technique
Existing whole reaction-type (integral-cover reaction) the nozzle level that covers at different levels is mounted to by a large amount of that the stator foundry goods that processes or the single reaction-type nozzle on the nozzle bearing form.More particularly, single nozzle is loaded in the dovetail groove, and is fixed on this bearing with the single pin that radially carries.Each nozzle tip is processed to have a kind of specific end sealing configuration of disturbing with this turbine rotor, so that reduce the steam leakage that takes place along this hot-gas channel to greatest extent.
In like manner, the existing whole reaction-type blade that covers at different levels is bound by the single radially bearing pins of a large amount of usefulness also that the single reaction-type blade that is fitted in the rotor forging that processes forms.After assembling, with these vanes fixed, these blade tips then are processed to this specific end sealing configuration with maintenance hardware.
The resulting cost that man-hour that the manufacturing of stator foundry goods, stator processing, nozzle blank and nozzle processing and stator assembling and rotor forging, rotor processing, blade blank, blade processing and assembling are spent and expense have increased the reaction-type stream passageway greatly.
The present invention's general introduction
According to exemplary embodiment of the present invention, simplified the manufacturing/assembly technology of nozzle and blade, reduce the overall cost of reaction-type stream passageway, and do not influenced the integrity of whole reaction-type steamturbine design.
In this exemplary embodiment, the flat blank of a full circle is processed whole row's reaction-type nozzle.Understand that above-mentioned blank can be annulus or a slab that forge, rolling.The annulus of this full circle is placed machining center, process its internal diameter, external diameter, inlet transition portion (inlet blend) aerofoil, aerofoil boundary, cover other standard details that ring seals configuration, the thin portion of maintenance and this nozzle.Spray nozzle plate that then should integral body is divided into the fan-shaped section of (also can not cutting apart) two or more arcs in order to carrying out the assembly process of last stream passageway.
In like manner, can process the reaction-type aerofoil of single-stage on the flat blank of a full circle, above-mentioned blank also can be rolling annulus or the slab that forges.The groove and tongue of the axial vane surface of also processed vane tip seal geometry, cooperation connects airtight and the thin portion of maintenance on this whole impeller.
Also adjacent stator and rotor surface can be merged into this integrated nozzle and impeller, it is stacked vertically in the mode of alternately arranging with respect to impeller that the latter is that a plurality of spray nozzle plates are convenient in the front and/or the back of nozzle and/or blade airfoil and being used for respectively.
Therefore, one aspect of the present invention relates to the integral wheel that is used for the turbine rotor parts, the impeller that comprises the full circle of making by the blank of a monoblock, the radially outer branch of this impeller is made with a plurality of blades, each blade have an airfoil portion and one radially outer end cover loop section, the inner radial branch of this impeller is made with the thin portion of one or more assemblings.
Another aspect of the present invention relates to a kind of integral wheel that is used for the reaction turbine rotor part, comprise the blank that the radially outer that is processed to have a plurality of blades having of a full circle divides, above-mentioned blade has an airfoil portion respectively and a radial outer end covers loop section; The inner radial branch of this blank is made with a plurality of anchor hole or bolts hole around this inner radial branch along circumferentially-spaced.
Another aspect of the present invention relates to the method for making turbine wheel, and this method comprises following steps: flat blank is made an annulus; The radially outer branch of this annulus is processed into has a plurality of blades that have an airfoil portion respectively; Then the inner radial branch of this annulus is processed into and has some and assemble thin portion.
Describe the present invention in detail below in conjunction with accompanying drawing.
The accompanying drawing summary
Fig. 1 is the perspective view by the integrated nozzle dish of exemplary embodiments of the present invention;
Fig. 2 is the perspective view by another kind of integrated nozzle dish of the present invention;
Fig. 3 is the spray nozzle plate perspective view that is assemblied in down the Fig. 1 in the turbine shroud;
Fig. 4 is the perspective view that is similar to Fig. 3, is placed in above the last fan-shaped section of spray nozzle plate but go up turbine shroud; With
Fig. 5 is the perspective view by the integral turbine impeller of rotor of another embodiment of the present invention.
Detailed description of the present invention
At first referring to Fig. 1, be divided into upper and lower two 180 ° the fan-shaped section integrated nozzle dish 10 of two half 12,14 in other words shown in the figure.Obviously, with diskware rive be convenient to into two be assembled to upper and lower turbine shroud parts in other words the part on, said nozzle dish fan-shaped section surrounds rotor part.
In this exemplary embodiment, spray nozzle plate 10 is formed by the flat blank manufacturing through forging and be rolled into annulus or slab of a full circle, and after this above-mentioned annulus is processed to have a plurality of aerofoils 16 that are circumferential arrangement at the inner radial branch of this spray nozzle plate.The radial inner end of aerofoil 16 also is processed to have a kind of integral body of this diskware internal diameter that determines and covers sealing configuration 18, the remaining part of diskware (being the radially outer branch specifically) 20 is processed into has the assembling bolt hole of usefulness or anchor hole 22 and any other flange or groove and tongue, with convenient and similar diskware or and the independent packing ring that holds between the diskware of rotatable platform of rotor part stacked vertically.
Fig. 2 illustrates another kind of integrated nozzle dish 24, the toroidal inlet 28 with a transition of extending vertically in the upstream of integrated nozzle 30 is processed in one side 26 of this diskware, radially outer at diskware 24 divides 34 also to process bolt hole or anchor hole 30, with convenient above-mentioned axially stacked.
Fig. 3 illustrates the spray nozzle plate 10 that is placed in down the Fig. 1 on the turbine shroud parts 36, and wherein, a plurality of grapplings or bolt 38 pass the hole 22 on the diskware 10, and are fixed by nut or other parts, so that a plurality of spray nozzle plate is axially stacked.
Fig. 4 illustrates the configuration of similar Fig. 3, but last turbine shroud parts 42 are assemblied in down on the turbine shroud parts 36, as can be seen, the upper and lower fan-shaped section 12,14 of spray nozzle plate and upper and lower turbine shroud parts 36,42 adopt conventional maintenance/tighten up the configuration (not shown) to be connected to each other respectively.At spray nozzle plate is under the situation of fan-shaped section configuration, and the fan-shaped section that meets the invention described above is also wanted the thin portion of processed this maintenance/tighten up.
Referring to Fig. 5, be processed into a reaction turbine impeller of rotor 44 by a flat slab material (forge and rolling annulus or slab), this impeller 44 processes a center hole 46, an inner radial divides 48 and radially outers to divide 50.Obviously, required geometrical shape can be processed into according to the size of associated rotor, shape etc. in hole 46.
The inner radial of impeller divides 48 to have the thin portion of connection part in the embodiment shown, comprises that a plurality of inner radial branches that center on are along circumference spaced bolt hole or anchor hole 52.Above-mentioned radially outer branch processes a plurality of turbine blades 54, and each blade has an airfoil portion 56 and an integral body is covered ring or top covering 58, and this top covering 58 is full circle along the radially outer end of whole airfoil portion 56.
As turbine nozzle dish 10 shown in Figure 1, impeller 44 also may be partitioned into two 180 ° fan-shaped section, so that assembling especially is beneficial to the on-the-spot single impeller of changing.Under other situation, impeller 44 does not separate, and assembles as the integral wheel of single full circle.
The adjacent rotors face also can be integrated in this impeller in the front and back of this blade airfoil part.For example, single adjacent rotor face (front or rear) can be merged in this impeller, and can be whole, or adds after this blade processing is become.In addition, paired adjacent rotor face (preceding and back) can be merged in this impeller, and can be whole, or adds after this aerofoil is processed into.Some application is without any need for additional adjacent rotor face.
Process this aerofoil according to top described method of the present invention, can eliminate following and the relevant obstacle of existing reaction-type Blade Design:
The interference problem of ring is covered in covering;
Ring taking apart in the opposite direction in the course of the work covered in covering;
Relate to the axial clearance problem of taking apart to a plurality of independent blade/pin of each grade assembling;
Need in manufacturing process, carry out such as reversing, extrude and the problem of the assembling check of throat area measurement etc.;
Need customary assembling modal test and the relevant funding problems of each test; With
About man-machine control relation for individual blade assembling dedicated bearer pin.
Except every above having solved, this integral wheel also can reach following purpose:
Improved the ability of a few row's blades of maintenance/repairing;
Set up known/boundary conditions repeatably;
Reduced the part count of each grade;
Reduced the departure in the assembling stage;
Reduced amount from the no materials (waste material) in blade and the rotor manufacture process;
Size, weight and the cost of rotor forging have been reduced;
Prevented to assemble in the parts and/or the direction of mistake;
Reduced to supporting manufacturing process, frock, operating device, check, program of seldom making and the required device resource amount of following of chance of errors; With
Compare with single blade, significantly reduced required quantity of material.
Though think most realistic the present invention to be described in conjunction with current above with illustrated embodiments, but understand, the invention is not restricted to described embodiment, but opposite, the present invention will comprise the various remodeling of the spirit and scope that meet claims and suitable configuration.
Label among the figure and title
10 nozzle dishes
16 blades
18 cover the sealing configuration
22 anchor holes or bolt hole
24 whole nozzle dishes
26 1 sides
The last fan-shaped section of 12 spray nozzle plates
The following fan-shaped section of 14 spray nozzle plates
32 bolts hole or anchor hole
34 radially outer branches
36 times turbine shroud parts
40 nuts
Turbine shroud parts on 42
44 impellers
46 center holes
48 inner radial branches
50 radially outer branches
52 spiral shell rifle hole or anchor holes
54 turbine blades
56 airfoil portions
58 cover ring or blade tip covering
Claims (10)
1. the integral wheel of turbine rotor parts (44), impeller with a full circle of making from a monoblock blank, the radially outer branch (50) of this impeller is made with a plurality of blades (54), each blade has an airfoil portion (56) and a radial tip outer cover ring part (58), and the inner radial branch (48) of above-mentioned impeller is made with the thin portion of one or more assemblings (52).
2. according to the integral wheel of claim 1, it is characterized in that above-mentioned assembly features comprises a plurality of anchor hole or bolts hole (52) that above-mentioned airfoil portion is radially inwardly located that are positioned at.
3. according to the integral wheel of claim 2, it is characterized in that above-mentioned anchor hole or bolt hole (52) center on above-mentioned inner radial branch (48) along spaced around.
4. according to the integral wheel of claim 1, it is characterized in that above-mentioned impeller (44) is divided into two or more fan-shaped section.
5. according to the integral wheel of claim 1, it is characterized in that above-mentioned blank comprises forging stock.
6. according to the integral wheel of claim 1, it is characterized in that above-mentioned blank comprises rolling ring blank.
7. according to the integral wheel of claim 1, it is characterized in that above-mentioned blank comprises the slab of general flat.
8. according to the integral wheel of claim 1, it is characterized in that this impeller (44) has a central hole (46) that is suitable for admitting a turbine rotor.
9. the integral wheel of a reaction turbine rotor part (44), comprise a blank that has the single full circle of the radially outer branch (50) that is processed to have a plurality of blades (54), above-mentioned blade (54) have respectively an airfoil portion (56) and one radially outer end cover loop section (58), inner radial branch (48) be processed to have a plurality of in its periphery along anchor hole or the bolt hole (52) of circle spacing.
10. a method of making turbine wheel (44) comprises following steps: flat blank is made a ring; Above-mentioned ring radially outer (50) is processed into has a plurality of blades (54); Each blade has airfoil portion (56) and the inner radial (48) of above-mentioned ring is processed into and has some and assemble thin portion (52).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/233057 | 2005-09-23 | ||
| US11/233,057 US20070071605A1 (en) | 2005-09-23 | 2005-09-23 | Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1936276A true CN1936276A (en) | 2007-03-28 |
Family
ID=37061444
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2006101395352A Pending CN1936276A (en) | 2005-09-23 | 2006-09-22 | Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20070071605A1 (en) |
| EP (1) | EP1767745A2 (en) |
| JP (1) | JP2007085351A (en) |
| CN (1) | CN1936276A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102741507A (en) * | 2010-02-04 | 2012-10-17 | 丰田自动车株式会社 | Turbocharger and turbocharger wheel housing |
| CN104181865B (en) * | 2014-08-27 | 2017-05-24 | 华中科技大学无锡研究院 | Annular feed path planning method of integral impeller rough machining |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060245923A1 (en) * | 2005-04-27 | 2006-11-02 | General Electric Company | Arcuate nozzle segment and related method of manufacture |
| US7497658B2 (en) * | 2005-11-11 | 2009-03-03 | General Electric Company | Stacked reaction steam turbine stator assembly |
| US20150098802A1 (en) * | 2013-10-08 | 2015-04-09 | General Electric Company | Shrouded turbine blisk and method of manufacturing same |
| USD842351S1 (en) * | 2018-01-23 | 2019-03-05 | Topline Corporation | Toroidal shaped particle impact damper |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2803397A (en) * | 1952-05-20 | 1957-08-20 | Gen Motors Corp | Compressor wheel |
| US3302926A (en) * | 1965-12-06 | 1967-02-07 | Gen Electric | Segmented nozzle diaphragm for high temperature turbine |
| US5043662A (en) * | 1990-10-25 | 1991-08-27 | Westinghouse Electric Corp. | Method and apparatus for producing a uniform magnetic field in a test sample |
| US5822841A (en) * | 1996-12-17 | 1998-10-20 | United Technologies Corporation | IBR fixture |
| JPH10245658A (en) * | 1997-03-05 | 1998-09-14 | Mitsubishi Heavy Ind Ltd | High cr precision casting material and turbine blade |
| US6095750A (en) * | 1998-12-21 | 2000-08-01 | General Electric Company | Turbine nozzle assembly |
| WO2000070509A1 (en) * | 1999-05-13 | 2000-11-23 | Rolls- Royce Corporation | Method for designing a cyclic symmetric structure |
| US20060245923A1 (en) * | 2005-04-27 | 2006-11-02 | General Electric Company | Arcuate nozzle segment and related method of manufacture |
-
2005
- 2005-09-23 US US11/233,057 patent/US20070071605A1/en not_active Abandoned
-
2006
- 2006-09-18 EP EP06254839A patent/EP1767745A2/en not_active Withdrawn
- 2006-09-22 JP JP2006256901A patent/JP2007085351A/en not_active Withdrawn
- 2006-09-22 CN CNA2006101395352A patent/CN1936276A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102741507A (en) * | 2010-02-04 | 2012-10-17 | 丰田自动车株式会社 | Turbocharger and turbocharger wheel housing |
| CN102741507B (en) * | 2010-02-04 | 2014-12-31 | 丰田自动车株式会社 | Turbocharger and turbocharger wheel housing |
| US9121281B2 (en) | 2010-02-04 | 2015-09-01 | Toyota Jidosha Kabushiki Kaisha | Turbocharger and turbocharger wheel housing |
| CN104181865B (en) * | 2014-08-27 | 2017-05-24 | 华中科技大学无锡研究院 | Annular feed path planning method of integral impeller rough machining |
Also Published As
| Publication number | Publication date |
|---|---|
| US20070071605A1 (en) | 2007-03-29 |
| JP2007085351A (en) | 2007-04-05 |
| EP1767745A2 (en) | 2007-03-28 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |