CN102748079B - Turbine outer ring device - Google Patents
Turbine outer ring device Download PDFInfo
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- CN102748079B CN102748079B CN201210247747.8A CN201210247747A CN102748079B CN 102748079 B CN102748079 B CN 102748079B CN 201210247747 A CN201210247747 A CN 201210247747A CN 102748079 B CN102748079 B CN 102748079B
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- turbine
- outer ring
- outer shroud
- ring device
- bulge loop
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Abstract
The invention discloses a turbine outer ring device which comprises an outer ring installation seat for being connected with a turbine motor box and an outer ring composed of more than two sector blocks. The outer ring is fixedly connected with the turbine motor box through the outer ring installation seat. The turbine outer ring device is used for greatly simplifying the processing difficulty and maintenance steps and increasing the production efficiency, and is convenient to assemble and disassemble.
Description
Technical field
The present invention relates to gas turbine field, especially, relate to a kind of turbine outer ring device.
Background technique
The turbine outer ring of gas turbine directly contacts with high-temperature fuel gas, and operating conditions is severe.Due to the erosion of Long-term Vibration, high temperature corrosion medium and the improper scraping of turbine blade-tip, make turbine outer ring inside coating be easy to come off, the effect of obturaging declines, and is one of parts that in gas turbine, repair rate is higher.
As shown in Figure 1 and Figure 2, common turbine outer ring 3 is uniformly distributed along the circumference and is formed by some sector units 12.Turbine outer ring 3 is connected the normal similar hook-shaped structure as shown in Figure 2 that adopts with turbine casing 1, turbine outer ring 3 front ends insert in the front hook annular groove 5 of turbine casing 1, rear end hangs between aft hook ring 7 and turbine casing 1, aft hook ring 7 is connected with turbine casing 1 by radial screw, turbine casing 1 is connected with nozzle ring 2, between turbine outer ring 3 and turbine blade 8, is provided with turbine blade-tip gap 9.
In above-mentioned structure, the sector unit of turbine outer ring 3 12 adopts independent packing, sector unit 12 and other component is mounted to the inner circle of wanting integral grinding turbine outer ring 3 after casing, to guarantee rational turbine blade-tip gap 9 after assembling; Numerous parts is combined and carried out internal grinding, parts fixation difficulty, technological operation is poor.As shown in Figure 2, because vibration, the erosion of high-temperature fuel gas and the scraping of turbine blade 8 blade tips cause the easy mill coating 6 of turbine outer ring 3 inner sides easily to come off, and while changing the sector unit 12 of turbine outer ring 3 a certain damages, dismantle turbine outer ring locating stud 4 and screw; Meanwhile, worm gear casing outside is also equiped with that other is fixed, the spacing component such as use, and all needs to disassemble; After assembling, equally also want grinding inner circle, complicated, the consuming time length of whole Renewal process and very inconvenience of operation processing.
Summary of the invention
The object of the invention be to provide a kind of simple in structure, technology capability good and the turbine outer ring device that is easy to change, to solve the technical problem of existing turbine outer ring difficult processing and dismounting inconvenience.
For achieving the above object, the invention provides a kind of turbine outer ring device, comprise: for the outer shroud fitting seat being connected with turbine casing and the outer shroud being comprised of plural sector unit, described outer shroud is fixedly connected with described turbine casing by described outer shroud fitting seat.
As a further improvement on the present invention:
Described outer shroud fitting seat comprises flange plate, and described flange plate is arranged on described turbine casing by axial bolt.
Described flange plate inner side is provided with vertically successively for the first annular groove and second annular groove of described outer shroud are installed, and is provided with vertically the first bulge loop and the second bulge loop on described outer shroud; Described the first bulge loop coordinates with described the first annular groove, and described the second bulge loop coordinates with described the second annular groove.
In described the first annular groove, interval is furnished with two above stop pins vertically, offers the pin-and-hole coordinating with described stop pin and described in each, on sector unit, be distributed with at least one pin-and-hole on described the first bulge loop.
On two end faces of described sector unit, all offer groove, two adjacent sector units connect by an airtight plate being arranged in described groove.
Described airtight plate is L shaped.
The two ends of described sector unit are along being circumferentially with boss and concave station, and described two adjacent sector units are connected by described boss and concave station.
The present invention has following beneficial effect:
1, turbine outer ring device of the present invention, the outer shroud that sector unit forms is installed by outer shroud fitting seat, according to the inner circle that requires grinding turbine outer ring device of turbine blade-tip gap, then turbine outer ring device is installed on turbine casing; Without being first installed on casing, regrinding and cut inner circle, greatly simplified the technology difficulty of processing.Outer shroud fitting seat adopts the structure of flange plate type to be directly arranged on vertically on turbine casing, when inside coating comes off, falls piece and causes turbine outer ring sector unit to change, only need the axial bolt on dismounting flange plate, easy accessibility, simplify maintenance step, improved manufacturing efficiency.
2, turbine outer ring device of the present invention, the outer shroud that sector unit forms and outer shroud fitting seat by the first bulge loop and the first annular groove coordinate and the second bulge loop was installed and is fixed with coordinating of the second annular groove, simple in structure, that part is processed is easy, cooperation reliably.Stop pin is set, can prevents that sector unit from rotating along circumferential on fitting seat, makes outer shroud more reliable with being connected of outer shroud fitting seat.
3, turbine outer ring device of the present invention, the airtight plate of being located between sector unit in groove connects, and can carry out block to high-temperature fuel gas, reduces high-temperature fuel gas and leaks from the joining place between sector unit.Or the mode that adopts boss and concave station to be connected between sector unit, also can reduce high-temperature fuel gas and leak from the joining place between sector unit.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the perspective view of the turbine outer ring of prior art;
Fig. 2 is the radial section structural representation of the turbine outer ring of prior art;
Fig. 3 is the perspective view of the turbine outer ring device of the preferred embodiment of the present invention 1;
Fig. 4 is the cross-sectional view of the turbine outer ring device of the preferred embodiment of the present invention 1;
Fig. 5 is the airtight plate of the preferred embodiment of the present invention 1 and the mounting structure schematic diagram of stop pin;
Fig. 6 is the sector unit composite structure schematic diagram of the preferred embodiment of the present invention 2.
Marginal data:
1, turbine casing; 2, nozzle ring; 3, turbine outer ring; 4, turbine outer ring locating stud; 5, front hook annular groove; 6, easily grind coating; 7, aft hook ring; 8, turbine blade; 9, turbine blade-tip gap; 10, outer shroud fitting seat; 101, flange plate; 102, the first annular groove; 103, the second annular groove; 104, stop pin; 11, outer shroud; 111, the first bulge loop; 112, the second bulge loop; 113, pin-and-hole; 12, sector unit; 121, groove; 122, boss; 123, concave station; 13, airtight plate.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
Embodiment 1:
As shown in Figure 2, Figure 3, Figure 4, turbine outer ring device of the present invention, comprise: for the outer shroud fitting seat 10 that is connected with turbine casing 1 with by plural (the present embodiment, quantity is three) outer shroud 11 that sector unit 12 forms, outer shroud 11 is fixedly connected with turbine casing 1 by outer shroud fitting seat 10.The outer shroud 11 that sector unit 12 forms is installed by outer shroud fitting seat 10, determines turbine outer ring device internal grinding amount, then the turbine outer ring device after internal grinding is installed on turbine casing 1 according to the requirement of turbine blade-tip gap 9; Without being first installed on casing, regrinding and cut inner circle, greatly simplified the technology difficulty of processing.
In the present embodiment, as shown in Figure 4, outer shroud fitting seat 10 comprises flange plate 101, and flange plate 101 is arranged on turbine casing 1 by axial bolt.Outer shroud fitting seat 10 adopts the structure of flange plate 101 formulas to be directly arranged on vertically on turbine casing 1, when inside coating comes off, falls sector unit 12 that piece causes turbine outer ring device and needs to change, only need the axial bolt on dismounting flange plate 101, easy accessibility, simplify maintenance step, improved manufacturing efficiency.Flange plate 101 inner sides are provided with vertically successively for the first annular groove 102 and second annular groove 103 of outer shroud 11 are installed, on outer shroud 11, be provided with vertically the first bulge loop 111 and second bulge loop 112(the first bulge loop 111 and the second bulge loop 112 and be all located at the outside of outer shroud 11, the inner side of outer shroud 11 is easy mill coating 6, easily grinds coating 6 and easily by turbine blade 8 blade tips, is scraped scrape along high-temperature fuel gas and wash away and come off); The first bulge loop 111 and the first annular groove 102 drive fits, during actual production, any one and corresponding annular groove drive fit in the first bulge loop 111 and the second bulge loop 112, another bulge loop and corresponding annular groove Spielpassung, can guarantee to install tautness, again can convenient operation.The outer shroud 11 that sector unit 12 forms and outer shroud 11 fitting seats 10 by the drive fit of bulge loop and annular groove install fixing, simple in structure, process easy, coordinate reliably.
In the present embodiment, as shown in Figure 5, in the first annular groove 102, interval is furnished with three stop pins 104 vertically, on the first bulge loop 111, offer on the pin-and-hole 113 that coordinates with stop pin 104 and each sector unit 12 and have a pin-and-hole 113, pin-and-hole 113 is preferably located at the circumferential middle part of each sector unit 12, can prevent that sector unit 12 from rotating along circumferential on fitting seat, makes outer shroud 11 more reliable with being connected of outer shroud fitting seat 10.
In the present embodiment, as shown in Figure 5, on two end faces of sector unit 12, all offer groove 121, two adjacent sector units 12 connect by an airtight plate 13 being arranged in groove 121.Airtight plate 13 is L shaped, can carry out block to high-temperature fuel gas, avoids high-temperature fuel gas to leak from the joining place between sector unit 12.Airtight plate 13 adopts high-temperature alloy material preparation.
Embodiment 2:
As shown in Figure 6, the turbine outer ring device of the present embodiment, its structure is substantially the same manner as Example 1, and the difference of the two is only, the two ends of sector unit 12 are along being circumferentially with boss 122 and concave station 123, and two adjacent sector units 12 are connected by boss 122 and concave station 123; Also can realize high-temperature fuel gas is carried out to block, avoid high-temperature fuel gas to leak from the joining place between sector unit 12.Other structures of the present embodiment are not repeating at this.
To sum up, turbine outer ring device of the present invention, simple in structure, technology capability good, assembling maintenance is good, and the turbine outer ring assembly that can quick integral changes the outfit, has simplified processing, assembling, decomposition technique and flow process.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (5)
1. a turbine outer ring device, it is characterized in that, comprise: for the outer shroud fitting seat (10) being connected with turbine casing (1) and the outer shroud (11) being comprised of plural sector unit (12), described outer shroud (11) is fixedly connected with described turbine casing (1) by described outer shroud fitting seat (10);
Described outer shroud fitting seat (10) comprises flange plate (101), and described flange plate (101) is arranged on described turbine casing (1) by axial bolt;
Described flange plate (101) inner side is provided with vertically successively for the first annular groove (102) and second annular groove (103) of described outer shroud (11) are installed, and is provided with vertically the first bulge loop (111) and the second bulge loop (112) on described outer shroud (11);
Described the first bulge loop (111) coordinates with described the first annular groove (102), and described the second bulge loop (112) coordinates with described the second annular groove (103).
2. turbine outer ring device according to claim 1, it is characterized in that, in described the first annular groove (102), interval is furnished with two above stop pins (104) vertically, offers the pin-and-hole (113) coordinating with described stop pin (104) and described in each, on sector unit (12), be distributed with at least one pin-and-hole (113) on described the first bulge loop (111).
3. turbine outer ring device according to claim 1 and 2, it is characterized in that, on two end faces of described sector unit (12), all offer groove (121), adjacent two sector units (12) connect by an airtight plate (13) being arranged in described groove (121).
4. turbine outer ring device according to claim 3, is characterized in that, described airtight plate (13) is L shaped.
5. turbine outer ring device according to claim 1 and 2, it is characterized in that, the two ends of described sector unit (12) are along being circumferentially with boss (122) and concave station (123), and adjacent two sector units (12) are connected by described boss (122) and concave station (123).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210247747.8A CN102748079B (en) | 2012-07-17 | 2012-07-17 | Turbine outer ring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210247747.8A CN102748079B (en) | 2012-07-17 | 2012-07-17 | Turbine outer ring device |
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| Publication Number | Publication Date |
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| CN102748079A CN102748079A (en) | 2012-10-24 |
| CN102748079B true CN102748079B (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210247747.8A Active CN102748079B (en) | 2012-07-17 | 2012-07-17 | Turbine outer ring device |
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| FR3051014B1 (en) * | 2016-05-09 | 2018-05-18 | Safran Aircraft Engines | TURBOMACHINE ASSEMBLY COMPRISING A DISTRIBUTOR, A TURBOMACHINE STRUCTURE ELEMENT, AND A FIXING DEVICE |
| CN109209517B (en) * | 2018-09-05 | 2021-03-16 | 中国航发动力股份有限公司 | Second-stage stationary blade ring assembly of self-adaptive thermal expansion of flue gas turbine |
| CN109578091B (en) * | 2018-11-23 | 2021-09-17 | 东方电气集团东方汽轮机有限公司 | Gas turbine cuts apart ring fixed knot and constructs |
| CN109882255B (en) * | 2019-03-01 | 2021-10-19 | 西安航天动力研究所 | Turbine stator top sealing limiting structure with blade type wire grooves |
| CN109751088A (en) * | 2019-03-25 | 2019-05-14 | 中国船舶重工集团公司第七0三研究所 | A kind of connecting structure of block-type turbine outer ring for marine gas turbine |
| CN114850799B (en) * | 2022-05-23 | 2023-04-18 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite turbine outer ring machining tool and machining method |
Citations (8)
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|---|---|---|---|---|
| US4909708A (en) * | 1987-11-12 | 1990-03-20 | Mtu Motoren- Und Turbinen- Union Munchen Gmbh | Vane assembly for a gas turbine |
| US5088888A (en) * | 1990-12-03 | 1992-02-18 | General Electric Company | Shroud seal |
| US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
| CN1664318A (en) * | 2004-03-04 | 2005-09-07 | Snecma发动机公司 | Axial maintenance device to support the strut of a stator ring of the high-pressure turbine of a turbomachine |
| CN1948718A (en) * | 2005-10-14 | 2007-04-18 | 通用电气公司 | Turbine shroud assembly and method for assembling a gas turbine engine |
| CN101046162A (en) * | 2006-03-30 | 2007-10-03 | 斯奈克玛 | Device for fixing ring sectors on the casing of a jet engine |
| JP4385660B2 (en) * | 2003-06-20 | 2009-12-16 | 株式会社Ｉｈｉ | Turbine shroud detent structure |
| CN101956576A (en) * | 2010-09-07 | 2011-01-26 | 沈阳斯特机械制造有限公司 | Radial inlet guide vane adjuster |
-
2012
- 2012-07-17 CN CN201210247747.8A patent/CN102748079B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4909708A (en) * | 1987-11-12 | 1990-03-20 | Mtu Motoren- Und Turbinen- Union Munchen Gmbh | Vane assembly for a gas turbine |
| US5088888A (en) * | 1990-12-03 | 1992-02-18 | General Electric Company | Shroud seal |
| US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
| JP4385660B2 (en) * | 2003-06-20 | 2009-12-16 | 株式会社Ｉｈｉ | Turbine shroud detent structure |
| CN1664318A (en) * | 2004-03-04 | 2005-09-07 | Snecma发动机公司 | Axial maintenance device to support the strut of a stator ring of the high-pressure turbine of a turbomachine |
| CN1948718A (en) * | 2005-10-14 | 2007-04-18 | 通用电气公司 | Turbine shroud assembly and method for assembling a gas turbine engine |
| CN101046162A (en) * | 2006-03-30 | 2007-10-03 | 斯奈克玛 | Device for fixing ring sectors on the casing of a jet engine |
| CN101956576A (en) * | 2010-09-07 | 2011-01-26 | 沈阳斯特机械制造有限公司 | Radial inlet guide vane adjuster |
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| CN102748079A (en) | 2012-10-24 |
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