CN104329124A - Novel positioning structure of turbine engine guider - Google Patents
Novel positioning structure of turbine engine guider Download PDFInfo
- Publication number
- CN104329124A CN104329124A CN201410700861.0A CN201410700861A CN104329124A CN 104329124 A CN104329124 A CN 104329124A CN 201410700861 A CN201410700861 A CN 201410700861A CN 104329124 A CN104329124 A CN 104329124A
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- China
- Prior art keywords
- positioning block
- positioning
- guide vane
- locating slot
- baffle
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Abstract
The invention discloses a novel positioning structure of a turbine engine guider. Hooks at large-diameter ends of guide vane sets are hung in grooves of cartridge receivers; the adjacent guide vane sets are connected together via the groove of the cartridge receiver and the hook; positioning blocks at the small-diameter ends of the guide vane sets extend into a positioning groove of a baffle; a pressing ring is fixed on the baffle via a screw and a locking plate; the positioning blocks of the guide vane sets are connected with the baffle and the pressing ring to form positioning grooves which are in clearance fit along the width direction; clearances are formed between the bottom parts of the positioning blocks and the positioning grooves; clearances among the stretching lengths of the positioning blocks, the bottom parts of the positioning blocks and the positioning grooves depend on that within the operation temperature variation range of the turbine engine, the positioning blocks are always positioned in the positioning grooves, and clearances are always formed in the bottom parts of the positioning blocks; the guide vane sets can stretch freely when are heated to be expanded without generating a stress concentration phenomenon and affecting the seal performance of a rotor and the baffle in the temperature variation process; the vibration frequency of the guide vane sets can be reduced; the service life can be prolonged; and the concentric requirement for the baffle can be met.
Description
technical field:
The present invention relates to Thermal Energy and Power Engineering control field, a kind of turbo machine thermal power transfer is the core component in mechanical energy systems, specifically a kind of novel turbo machine guider position structure.
background technique:
In the turbine, as long as multistage turbine structure all can run into cantilevered nozzle ring structure, the effect of nozzle ring is accelerated except gas and leading role except flow passage component expands, and its underpart dividing plate also has the seal action of isolated two chambers.Cantilevered nozzle ring is in high temperature, under hyperbaric environment, the power that path place is subject to all can be exaggerated at the force bearing point at large footpath place, stress when solving thermal expansion is one of subject matter of nozzle ring design, the bigger diameter end of guider is all fixed in the groove of interior casing with the Spielpassung form of hanger type, this structure also can make guider need in the design to solve vibration problem, the stator blade of turbo machine is in high temperature, under the rugged environment of high pressure, subject aerodynamic force, thermal stress and vibrational loading, for cooled blade or the hollow-core construction of thin-walled, necessary proof strength, the safety stock of vibration, so the overall force-bearing situation improving guider is necessary.
summary of the invention:
The object of the present invention is to provide a kind of novel guider position structure, this structure can effectively improve the stressed of stator blade and Vibration Condition, increases the working life of blade, improves the reliability of complete machine.
Technological scheme of the present invention is: novel turbo machine guider position structure, comprise casing and stator group, the hook of stator group bigger diameter end hangs in the groove of casing, be connected together by the groove of casing and hook connecting between adjacent guide vane group, two adjacent vane group counterfaces install Stamping Steel Ribbon additional, the positioning block of stator group miner diameter end stretches in the locating slot of dividing plate, pressure ring is fixed on dividing plate by screw and locking plate, and between the locating slot that the positioning block of stator group and dividing plate and pressure ring are connected to form, width direction is Spielpassung.
The positioning block of described stator group miner diameter end stretches in the locating slot of dividing plate, space is there is bottom positioning block and between locating slot, space bottom the length that positioning block stretches into and positioning block and between locating slot is depended on: in the range of temperature of turbine rotor, positioning block is positioned at locating slot all the time, there is space all the time bottom positioning block.
The present invention has following beneficial effect: can free-extension during stator group expanded by heating footpath, stress concentration phenomenon can not be produced, and in the process of temperature variation, do not have influence on the sealability of rotor and dividing plate, the vibration frequency of stator group can be reduced, improve working life, meet the concentric requirement needed for dividing plate.
accompanying drawing illustrates:
Fig. 1 is structural representation of the present invention.
1-casing in figure; 2-stator group; 3-pressure ring; 4-screw; 5-locking plate; 6-dividing plate; 7-positioning block; 8-locating slot; 9-links up with; 10-rotor, 11-Stamping Steel Ribbon.
embodiment:
Below in conjunction with accompanying drawing, the invention will be further described:
As shown in Figure 1, novel turbo machine guider position structure, comprise casing 1 and stator group 2, the hook 9 of stator group 2 bigger diameter end hangs in the groove of casing 1, linked together by the groove of casing 1 and hook 9 between adjacent guide vane group 2, two adjacent vane group 2 counterfaces install Stamping Steel Ribbon 11 additional, the positioning block 7 of stator group 2 miner diameter end stretches in the locating slot 8 of dividing plate 6, pressure ring 3 is fixed on dividing plate 6 by screw 4 and locking plate 5, and between the locating slot 8 that the positioning block 7 of stator group 2 and dividing plate 6 and pressure ring 3 are connected to form, width direction is Spielpassung.
The positioning block 7 of described stator group 2 miner diameter end stretches in the locating slot 8 of dividing plate 6, space is there is bottom positioning block 7 and between locating slot 8, space bottom the length that positioning block 7 stretches into and positioning block 7 and between locating slot 8 is depended on: in the range of temperature of turbine rotor, positioning block 7 is positioned at locating slot 8 all the time, there is space all the time bottom positioning block 7.
The stator group 2 of one number of turns band positioning block and the dividing plate 6 of band locating slot 8, pressure ring 3 and dividing plate 6 is connected with screw 4, whole circle stator group 2 is pressed between pressure ring 3 and dividing plate 6, stator group 2 positioning block 7 coordinates with dividing plate 6 locating slot 8 and is assembled together, form entire combination part, the bigger diameter end of stator group 2 is fixed on casing 1 by arc hook.
During stator group 2 expanded by heating radial extent, can free-extension, stator group 2 positioning block 7 radially can slide in dividing plate 6 locating slot 8, not by the constraint of dividing plate 6, pressure ring 3, so stress concentration phenomenon can not be produced, and can not change in the process central diaphragm 6 of temperature variation, pressure ring 3 central position, and then the sealability of rotor 10 and dividing plate can not be had influence on.
The vibration frequency of stator group 2 can be reduced, improve working life, guider is a cantilever structure, power suffered on it finally all needs to be delivered on the hook 9 that bigger diameter end is connected with casing 1, self rigidity of guider has great impact to its resistance to shock, due to one week, several stator group 2 was fixed as a whole by dividing plate 6 pressure ring 3, when before and after stator blade or dividing plate, the pressure of local changes, local compression can be distributed on whole coil structures by this structure, suppress vibration, improve the integral rigidity of guider and the working life of blade, must with the positioning block 7 in specific precision and fit system processing stator group 2 and the locating slot 8 on dividing plate 6, during such guarantee expanded by heating, dividing plate 6 center does not offset, meet required concentric requirement.
Claims (2)
1. a novel turbo machine guider position structure, comprise casing (1) and stator group (2), it is characterized in that: the hook (9) of stator group (20) bigger diameter end hangs in the groove of casing (1), linked together by the groove of casing (1) and hook (9) between adjacent guide vane group (2), two adjacent vane group (2) counterfaces install Stamping Steel Ribbon (11) additional, the positioning block (7) of stator group (2) miner diameter end stretches in the locating slot (8) of dividing plate (6), pressure ring (3) is fixed on dividing plate (6) by screw (4) and locking plate (5), between the locating slot (8) that the positioning block (7) of stator group (2) and dividing plate (6) and pressure ring (3) are connected to form, width direction is Spielpassung.
2. novel turbo machine guider position structure according to claim 1, it is characterized in that: the positioning block (7) of stator group (2) miner diameter end stretches in the locating slot (8) of dividing plate (6), space is there is between positioning block (7) bottom and locating slot (8), the length that positioning block (7) stretches into and the space between positioning block (7) bottom and locating slot (8) are depended on: in the range of temperature of turbine rotor, positioning block (7) is positioned at locating slot (8) all the time, and positioning block (7) bottom exists space all the time.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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CN201410700861.0A CN104329124A (en) | 2014-11-28 | 2014-11-28 | Novel positioning structure of turbine engine guider |
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CN201410700861.0A CN104329124A (en) | 2014-11-28 | 2014-11-28 | Novel positioning structure of turbine engine guider |
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CN104329124A true CN104329124A (en) | 2015-02-04 |
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CN201410700861.0A Pending CN104329124A (en) | 2014-11-28 | 2014-11-28 | Novel positioning structure of turbine engine guider |
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Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
CN105464717A (en) * | 2015-12-25 | 2016-04-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Stator blade circumferential stop mechanism |
CN109057877A (en) * | 2018-10-26 | 2018-12-21 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine stators structure |
CN109469514A (en) * | 2018-12-28 | 2019-03-15 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine partition pressure ring sealing device |
CN111535869A (en) * | 2020-04-29 | 2020-08-14 | 中国航发湖南动力机械研究所 | Turbine guide |
CN111794807A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
CN113931872A (en) * | 2021-12-15 | 2022-01-14 | 成都中科翼能科技有限公司 | Double-layer drum barrel reinforced rotor structure of gas compressor of gas turbine |
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US2488867A (en) * | 1946-10-02 | 1949-11-22 | Rolls Royce | Nozzle-guide-vane assembly for gas turbine engines |
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CN1894485A (en) * | 2003-11-20 | 2007-01-10 | 通用电气公司 | Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction |
CN103195498A (en) * | 2012-01-05 | 2013-07-10 | 通用电气公司 | System and method for sealing a gas path in a turbine |
US20130209249A1 (en) * | 2012-02-09 | 2013-08-15 | Snecma | Annular anti-wear shim for a turbomachine |
CN204225959U (en) * | 2014-10-31 | 2015-03-25 | 徐工集团工程机械股份有限公司江苏徐州工程机械研究院 | A kind of road roller silencing apparatus baffle arrangement |
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2014
- 2014-11-28 CN CN201410700861.0A patent/CN104329124A/en active Pending
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US2488867A (en) * | 1946-10-02 | 1949-11-22 | Rolls Royce | Nozzle-guide-vane assembly for gas turbine engines |
US4384822A (en) * | 1980-01-31 | 1983-05-24 | Motoren- Und Turbinen-Union Munchen Gmbh | Turbine nozzle vane suspension for gas turbine engines |
CN1894485A (en) * | 2003-11-20 | 2007-01-10 | 通用电气公司 | Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction |
CN103195498A (en) * | 2012-01-05 | 2013-07-10 | 通用电气公司 | System and method for sealing a gas path in a turbine |
US20130209249A1 (en) * | 2012-02-09 | 2013-08-15 | Snecma | Annular anti-wear shim for a turbomachine |
CN204225959U (en) * | 2014-10-31 | 2015-03-25 | 徐工集团工程机械股份有限公司江苏徐州工程机械研究院 | A kind of road roller silencing apparatus baffle arrangement |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105397465B (en) * | 2015-12-08 | 2017-05-31 | 四川成发航空科技股份有限公司 | For the device of engine turbine assembling |
CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
CN105464717A (en) * | 2015-12-25 | 2016-04-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Stator blade circumferential stop mechanism |
CN109057877A (en) * | 2018-10-26 | 2018-12-21 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine stators structure |
CN109057877B (en) * | 2018-10-26 | 2023-11-28 | 中国船舶重工集团公司第七0三研究所 | Turbine stator structure for helium turbine |
CN109469514A (en) * | 2018-12-28 | 2019-03-15 | 中国船舶重工集团公司第七0三研究所 | A kind of helium turbine partition pressure ring sealing device |
CN111535869B (en) * | 2020-04-29 | 2022-07-29 | 中国航发湖南动力机械研究所 | Turbine guide |
CN111535869A (en) * | 2020-04-29 | 2020-08-14 | 中国航发湖南动力机械研究所 | Turbine guide |
CN111794807A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
CN111794807B (en) * | 2020-06-24 | 2022-01-11 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
CN113931872A (en) * | 2021-12-15 | 2022-01-14 | 成都中科翼能科技有限公司 | Double-layer drum barrel reinforced rotor structure of gas compressor of gas turbine |
CN113931872B (en) * | 2021-12-15 | 2022-03-18 | 成都中科翼能科技有限公司 | Double-layer drum barrel reinforced rotor structure of gas compressor of gas turbine |
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Application publication date: 20150204 |