CN201539279U - Large-scale air cooled steam turbine last-stage blade - Google Patents
Large-scale air cooled steam turbine last-stage blade Download PDFInfo
- Publication number
- CN201539279U CN201539279U CN2009202778197U CN200920277819U CN201539279U CN 201539279 U CN201539279 U CN 201539279U CN 2009202778197 U CN2009202778197 U CN 2009202778197U CN 200920277819 U CN200920277819 U CN 200920277819U CN 201539279 U CN201539279 U CN 201539279U
- Authority
- CN
- China
- Prior art keywords
- blade
- section
- positioning section
- root
- locating ring
- 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.)
- Expired - Lifetime
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a large-scale air cooled steam turbine last-stage blade. The height L of a molded line portion 2 of the blade is 510mm; the molded line of the blade is a twisted blade with variable cross sections; each cross section along blade height is different in shape; the areas of the cross sections are decreased; torsion is arranged between adjacent cross sections; a blade root is in the shape of an inclined fir tree; axial width B is 182mm; the total height (H1) of the blade root is 64.23mm; an integrally shrouded band is arranged on a blade top; and a plurality of sealing teeth can be assembled on the top portion of the blade to prevent air leakage and improve unit efficiency. The blade is used for the last stage of an air cooled unit, and both economical efficiency and safety reliability of running can reach advanced level.
Description
Technical field
The utility model relates to a kind of air cooling turbine exhaust stage blade, particularly large air-cooled turbine machine exhaust stage blade.
Background technique
Air-cooled Unit is a kind of typical variable parameter operation unit, compare with clammy unit, its back pressure is subjected to the influence of ambient temperature more much bigger than the latter, the design back pressure height and the excursion of Air-cooled Unit are big, exhaust stage blade is worked under the condition of the very severe of being everlasting, aeroperformance and strength character to blade are all had higher requirement, so the Air-cooled Unit exhaust stage blade is wanted particular design.
The model utility content
The purpose of this utility model provides a kind of large air-cooled turbine machine exhaust stage blade, to solve existing large air-cooled turbine machine last stage movable vane tablet quality instability, inefficiency, the uneasy congruent problem of working procedure.
For achieving the above object, technical solution of the present utility model is:
A kind of large air-cooled turbine machine exhaust stage blade comprises shroud (1), vane type line part (2), lacing wire (3) and blade root (4); Shroud (1), vane type line part (2) and blade root (4) die forging from top to bottom are integral, and vane type line part (2) is the variable cross section twisted blade, reduces gradually to the top cross-section area from root, has relatively between adjacent two sections and reverses; The height L of its vane type line part (2) is 510mm, and the root axial width (B0) of vane type line part (2) is 156.02mm, and the apical axis of vane type line part (2) is 57.84mm to width (B1); Vane type line part (2) cross section geometric data from root to the top are: cross section number (A-A) depth of section of number (Q-Q) is 510mm to the cross section, axial width B is 155.996～57.839mm, chord length b is 167.424～133.207mm, established angle is 69.243～25.569 degree, flow outlet angle is 23.438～18.97 degree, and section area is 42.67～8.05cm
2, maximum ga(u)ge (O) is 37.6～9.5mm, trailing edge thickness (δ) is 3.85～1.73mm.
Described large air-cooled turbine machine exhaust stage blade, its described blade root (4) is oblique fir-tree root, and axial width (B) is 182mm, and the total height (H1) of blade root (4) is 64.23mm.
Described large air-cooled turbine machine exhaust stage blade, its described lacing wire (3) is a pattern of partly cuing open loose lacing wire.
Described large air-cooled turbine machine exhaust stage blade, the gap (W1) between its described adjacent shroud (1) between working surface A, the B is 0～0.03mm, the gap (W3) between the gap between non-working surface C, the D (W2) and E, the F is 0.2～0.5mm.
Described large air-cooled turbine machine exhaust stage blade, it is described to be provided with the axially locating ring on the abutted surface of blade root (4) and impeller (6), with the axially locating ring that a plurality of exhaust stage blades and impeller (6) are affixed;
The axially locating ring is connected to form in proper order by most arc positioning sections; A most positioning section are the T shape of side, are divided into common positioning section and seal positioning section, and common positioning section is a plurality of, and sealing positioning section is one;
A plurality of common positioning sections are divided into three kinds according to length: a kind of is a pitch, second kind is two pitches, and the third is four pitches; Common positioning section is made of the arc L shape first half and arc L shape Lower Half, and the upper and lower half is amplexiformed into the T shape segmental arc of side up and down, and abutted surface each other is the plane;
An arc seals positioning section, and its length is a pitch, is made of the arc L shape first half and arc L shape Lower Half, the relative up and down face in upper and lower half is the plane, and two interplanars have a gap, an arcuation bar shaped sprue, its length and gap are suitable, are positioned at the gap; Seal the positioning section first half, sprue, seal the T shape segmental arc that the positioning section Lower Half is amplexiformed into side up and down;
On blade root and impeller abutted surface, be provided with and the suitable groove of axially locating ring at the wheel rim place of blade root bottom, impeller;
Behind the location, the axially locating ring is positioned at the groove at blade root bottom, wheel rim place, and is fixing with welding between the upper and lower half of sealing positioning section and the sprue.
Described large air-cooled turbine machine exhaust stage blade, its described axially locating ring comprises one of the common positioning section of a pitch, three of the common positioning sections of two pitches, 14 of the common positioning sections of four pitches seal one of positioning section, and end-to-end constitutes a whole axially locating ring; Behind the location, the first half of most positioning sections is in the groove of blade root bottom, and Lower Half is in the groove at wheel rim place, and is fixing with welding between the upper and lower half of sealing positioning section and the sprue.
The utility model has the advantages that: one. the utility model adopts the angle of attack and all insensitive blade profile of Mach number, adjust degree of reaction distribution radially simultaneously meticulously, the Security and the high efficiency of blade are organically combined, make this blade have stronger variable working condition characteristic, thereby guarantee that unit under variable working condition, also can move efficiently and safely; Two, the utility model adopts the blade profile of strengthening, and makes this blade can stand the test of abominable operating conditions; Three, exhaust stage blade employing shroud (1) of the present utility model, vane type line part (2) are the structural type of one with blade root (4), assemble very convenient, when static, be gapped between the link, during work, under action of centrifugal force, form whole circle link by twist recovery between the blade; Four, the utility model adopts the mode of edge Si Taili alloy slice 5 to prevent the adverse effect of water erosion wearing and tearing to blade Security and unit economy; Five, vane tip of the present utility model adopts and carries shroud, and the problem of stress concentration that does not exist riveted joint to cause is reduced the loss, and the multi-disc gland sealing gear can be assembled in the top, prevents gas leakage, improves unit efficiency.Six, the utility model adopts oblique fir tree blade root, and the fit of blade is for axially packing into, and the axially locating of blade root and wheel rim adopts the structure of axially locating ring.
Description of drawings
Fig. 1 is the overall structure schematic representation of a kind of large air-cooled turbine machine of the utility model exhaust stage blade;
Fig. 2 is the right elevation of Fig. 1;
Fig. 3 is the plan view of Fig. 1;
Fig. 4 is the plan view of vane type line part;
Fig. 5 is the axially locating mode schematic representation of blade root and wheel rim; Wherein:
Fig. 5 a is the connection diagram of blade root and wheel rim;
Fig. 5 b is the structural representation of axially locating ring;
Fig. 5 c is the cross-sectional schematic of axially locating ring; Wherein, A-A represents the sectional view at the common positioning section of axially locating ring place;
Fig. 5 d is the cross-sectional schematic of axially locating ring; Wherein, B-B analyses and observe the sectional view of expression axially locating ring seal mouth position;
Fig. 6 is the superimposed figure of molded lines of a kind of large air-cooled turbine machine of the utility model exhaust stage blade;
Fig. 7 requires schematic representation for shroud cooperates.
Embodiment
See Fig. 1, Fig. 2, Fig. 3 and shown in Figure 4, a kind of novel last-stage moving blade of air-cooled steam turbine comprises blade profile part, leaf root part, leaf top part.Wherein:
(1) movable vane is the variable cross section twisted blade, is reduced gradually by the section area of root to the top along blade height, reverses between the adjacent two sections.
(2) blade root is high-intensity oblique fir tree blade root, and the fit of blade is axially assembling, and the axially locating of blade root and wheel rim adopts the structure (seeing for details shown in Figure 5) of axially locating ring.
(3) lacing wire of leaf top part and shroud are respectively and partly cut open lacing wire, self-crown damping shroud.
The height L of vane type line part (2) is 510mm, and the root axial width (B0) of vane type line part (2) is 156.02mm, and the apical axis of vane type line part (2) is 57.84mm to width (B1).Referring to Fig. 6, A-A wherein, I-I, Q-Q represent cross section number.Vane type line part (2) cross section geometric data from root to the top: cross section number (A-A) depth of section of number (Q-Q) is 510mm to the cross section, axial width B is 155.996～57.839mm, chord length b is 167.424～133.207mm, established angle is 69.243～25.569 degree, flow outlet angle is 23.438～18.97 degree, and section area is 42.67～8.05cm
2, maximum ga(u)ge (O) is 37.6～9.5mm, trailing edge thickness (δ) is 3.85～1.73mm.
Concrete parameter in each cross section such as table 1:
Table 1
| Cross section number | Depth of section L (mm) | Axial width B (mm) | Chord length b (mm) | Established angle (degree) | Flow outlet angle (degree) | Section area (cm 2) | Maximum ga(u)ge O (mm) | Trailing edge thickness δ (mm) |
| A-A | 0.0 | 155.996 | 167.424 | 69.243 | 23.438 | 42.67 | 37.6 | 3.85 |
| C-C | 63.75 | 147.538 | 161.815 | 66.210 | 23.438 | 35.87 | 32.1 | 3.64 |
| E-E | 127.5 | 137.745 | 154.903 | 63.148 | 23.086 | 30.24 | 28.2 | 3.44 |
| G-G | 191.25 | 125.566 | 149.139 | 57.601 | 22.683 | 24.05 | 24.5 | 3.09 |
| I-I | 255.0 | 111.647 | 145.121 | 50.474 | 22.505 | 17.97 | 20.4 | 2.52 |
| K-K | 318.75 | 96.958 | 143.195 | 42.890 | 21.444 | 13.51 | 16.8 | 1.83 |
| M-M | 382.5 | 81.788 | 141.643 | 35.382 | 20.837 | 10.29 | 12.6 | 1.75 |
| O-O | 446.25 | 69.221 | 139.348 | 29.808 | 20.191 | 8.80 | 10.5 | 1.86 |
| Q-Q | 510.0 | 57.839 | 133.207 | 25.569 | 18.970 | 8.05 | 9.5 | 1.73 |
Blade root (4) is oblique fir-tree root, and axial width (B) is 182mm.The total height of blade root (H1) is 64.23mm.
Lacing wire (3) is a pattern of partly cuing open loose lacing wire.
See shown in Figure 7ly, the gap W1 between the adjacent shroud (1) between working surface A, the B is 0～0.03mm, and gap W2 between non-working surface C, the D and the gap W3 between E, the F are 0.2～0.5mm.
See that Fig. 5 is blade root and wheel rim axially locating mode schematic representation, wherein, Fig. 5 a is the connection diagram of blade root 4 and wheel rim 6, Fig. 5 b is the structural representation of axially locating ring, Fig. 5 c is the cross-sectional schematic of axially locating ring, and wherein, A-A represents the sectional view at the common positioning section of axially locating ring place; B-B analyses and observe the sectional view of expression axially locating ring seal mouth position.As shown in the figure, the axially locating of blade root 4 and wheel rim 6 adopts the mode of axially locating ring, and the axially locating ring is the T shape of side, is connected to form a whole axially locating ring in proper order by most arc positioning sections.A most positioning section all are the T shapes of side, are divided into common positioning section 7 and seal 8 two kinds of positioning sections, and the common positioning section 7 of arc has a plurality of, and arc seals positioning section 8 and has only one.
The common positioning section 7 of a plurality of arcs is divided into three kinds according to length: a kind of is a pitch, second kind is two pitches, and the third is four pitches.Common positioning section 7 is made of arc L shape first half 7a and arc L shape Lower Half 7b, and upper and lower half 7a, 7b amplexiform into the T shape segmental arc of side up and down, and abutted surface each other is the plane.
An arc seals positioning section 8, its length is a pitch, constitute by arc L shape first half 8a and arc L shape Lower Half 8b, the face that upper and lower half 8a, 8b are relative up and down is the plane, two interplanars have a gap, one arcuation bar shaped sprue 9, its length and gap are suitable, are positioned at the gap.First half 8a, sprue 9, Lower Half 8b amplexiform into the T shape segmental arc of side up and down.
On blade root 4 and impeller 6 abutted surfaces, the wheel rim place of blade root 4 bottoms, impeller 6 is provided with and the suitable groove of axially locating ring.
In the present embodiment, the quantity of exhaust stage blade is 64.Its axially locating ring comprises 7 one of the common positioning sections of a pitch, 7 three of the common positioning sections of two pitches, and 70 four of the common positioning sections of four pitches seal 8 one of positioning sections.Seal positioning section 8 orders by these common positioning sections 7 and one and be connected to form a whole axially locating ring.According to above-mentioned, the quantity of exhaust stage blade is: 1+2x3+4x14+1=64 only.
Concrete fit is, common positioning section 7 and the first half 7a, the 8a that seal positioning section 8 pack in blade root 4 bottom grooves, and in the wheel rim place of impeller 6 groove, pack into common positioning section 7 and the Lower Half 7b, the 8b that seal positioning section 8, after whole circle axially locating ring installs, sprue 9 is inserted the gap of sealing between positioning section 8 upper and lower half 8a, the 8b, and weld with fixing.
Claims (6)
1. a large air-cooled turbine machine exhaust stage blade comprises shroud (1), vane type line part (2), lacing wire (3) and blade root (4); Shroud (1), vane type line part (2) and blade root (4) die forging from top to bottom are integral, and vane type line part (2) is the variable cross section twisted blade, reduces gradually to the top cross-section area from root, has relatively between adjacent two sections and reverses; It is characterized in that: the height L of vane type line part (2) is 510mm, and the root axial width (B0) of vane type line part (2) is 156.02mm, and the apical axis of vane type line part (2) is 57.84mm to width (B1); Vane type line part (2) cross section geometric data from root to the top are: cross section number (A-A) depth of section of number (Q-Q) is 510mm to the cross section, axial width B is 155.996～57.839mm, chord length b is 167.424～133.207mm, established angle is 69.243～25.569 degree, flow outlet angle is 23.438～18.97 degree, and section area is 42.67～8.05cm
2, maximum ga(u)ge (O) is 37.6～9.5mm, trailing edge thickness (δ) is 3.85～1.73mm.
2. large-size steam turbine exhaust stage blade according to claim 1 is characterized in that: described blade root (4) is oblique fir-tree root, and axial width (B) is 182mm, and the total height (H1) of blade root (4) is 64.23mm.
3. large-size steam turbine exhaust stage blade according to claim 1 is characterized in that: described lacing wire (3) is a pattern of partly cuing open loose lacing wire.
4. large-size steam turbine exhaust stage blade according to claim 1, it is characterized in that: the gap (W1) between the described adjacent shroud (1) between working surface A, the B is 0～0.03mm, and the gap (W3) between the gap between non-working surface C, the D (W2) and E, the F is 0.2～0.5mm.
5. large-size steam turbine exhaust stage blade according to claim 1 is characterized in that: describedly on the abutted surface of blade root (4) and impeller (6), be provided with the axially locating ring, and with the axially locating ring that a plurality of exhaust stage blades and impeller (6) are affixed;
The axially locating ring is connected to form in proper order by most arc positioning sections; A most positioning section are the T shape of side, are divided into common positioning section and seal positioning section, and common positioning section is a plurality of, and sealing positioning section is one;
A plurality of common positioning sections are divided into three kinds according to length: a kind of is a pitch, second kind is two pitches, and the third is four pitches; Common positioning section is made of the arc L shape first half and arc L shape Lower Half, and the upper and lower half is amplexiformed into the T shape segmental arc of side up and down, and abutted surface each other is the plane;
An arc seals positioning section, and its length is a pitch, is made of the arc L shape first half and arc L shape Lower Half, the relative up and down face in upper and lower half is the plane, and two interplanars have a gap, an arcuation bar shaped sprue, its length and gap are suitable, are positioned at the gap; Seal the positioning section first half, sprue, seal the T shape segmental arc that the positioning section Lower Half is amplexiformed into side up and down;
On blade root and impeller abutted surface, be provided with and the suitable groove of axially locating ring at the wheel rim place of blade root bottom, impeller;
Behind the location, the axially locating ring is positioned at the groove at blade root bottom, wheel rim place, and is fixing with welding between the upper and lower half of sealing positioning section and the sprue.
6. large-size steam turbine exhaust stage blade according to claim 1, it is characterized in that: described axially locating ring, one of the common positioning section that comprises a pitch, three of the common positioning sections of two pitches, 14 of the common positioning sections of four pitches, seal one of positioning section, end-to-end constitutes a whole axially locating ring; Behind the location, the first half of most positioning sections is in the groove of blade root bottom, and Lower Half is in the groove at wheel rim place, and is fixing with welding between the upper and lower half of sealing positioning section and the sprue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202778197U CN201539279U (en) | 2009-11-25 | 2009-11-25 | Large-scale air cooled steam turbine last-stage blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202778197U CN201539279U (en) | 2009-11-25 | 2009-11-25 | Large-scale air cooled steam turbine last-stage blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201539279U true CN201539279U (en) | 2010-08-04 |
Family
ID=42590733
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202778197U Expired - Lifetime CN201539279U (en) | 2009-11-25 | 2009-11-25 | Large-scale air cooled steam turbine last-stage blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201539279U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102434223A (en) * | 2011-12-13 | 2012-05-02 | 杭州汽轮机股份有限公司 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
-
2009
- 2009-11-25 CN CN2009202778197U patent/CN201539279U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102434223A (en) * | 2011-12-13 | 2012-05-02 | 杭州汽轮机股份有限公司 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
| CN102434223B (en) * | 2011-12-13 | 2014-08-20 | 杭州汽轮机股份有限公司 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4785511B2 (en) | Turbine stage | |
| US6471474B1 (en) | Method and apparatus for reducing rotor assembly circumferential rim stress | |
| US6506022B2 (en) | Turbine blade having a cooled tip shroud | |
| AU2007214378B2 (en) | Methods and apparatus for fabricating turbine engines | |
| CA2783436C (en) | Cap for ceramic blade tip shroud | |
| CN100489277C (en) | Methods and apparatus for cooling gas turbine rotor blades | |
| JP2012052526A (en) | Shrouded turbine blade with contoured platform and axial dovetail | |
| CN103216271B (en) | turbomachine blade tip shroud | |
| CN201581936U (en) | Special last-stage vane for large-scale 60Hz turbine | |
| US9347320B2 (en) | Turbine bucket profile yielding improved throat | |
| JP7341683B2 (en) | Tip shroud fillet for turbine rotor blades | |
| EP1748155A3 (en) | Cooled shroud assembly and method of cooling a shroud | |
| US20130004290A1 (en) | Turbo-Machinery With Flow Deflector System | |
| CN106256993A (en) | A kind of final stage moving blade of feed pump industrial steam turbine | |
| CN201125750Y (en) | Large-sized complete rotary speed 60Hz steam turbine last stage blade | |
| CN201539279U (en) | Large-scale air cooled steam turbine last-stage blade | |
| JP2013151935A (en) | Turbine packing deflector | |
| CN201606119U (en) | Large steam turbine last-stage blade | |
| CN204532440U (en) | Nozzle assembly and rotating machinery | |
| CN2711391Y (en) | Final stage blade for large air cooling turbine | |
| CN106194276A (en) | Compressor assembly and airfoil assembly | |
| JP2015525853A (en) | Turbine blade | |
| CN2883679Y (en) | Final blade of large-scale air cooling turbine | |
| CN201620917U (en) | Last-stage moving blade of large stream turbine | |
| CN201507325U (en) | Large-size turbine last stage blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20100804 |
|
| CX01 | Expiry of patent term |