CN104454026A - Zigzag-shroud of aero-engine rotor vane - Google Patents
Zigzag-shroud of aero-engine rotor vane Download PDFInfo
- Publication number
- CN104454026A CN104454026A CN201410624101.6A CN201410624101A CN104454026A CN 104454026 A CN104454026 A CN 104454026A CN 201410624101 A CN201410624101 A CN 201410624101A CN 104454026 A CN104454026 A CN 104454026A
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- rotor blade
- shroud
- sawtooth
- zigzag
- leaf grating
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to an engine vane structure, in particular to a zigzag-shroud of an aero-engine rotor vane. According to the technical scheme, the zigzag-shroud is located at the upper end of the rotor vane, a labyrinth seal and a rectification blade cascade are arranged on the upper surface of the zigzag-shroud, the labyrinth seal is located at the rear end of the upper surface of the zigzag-shroud, the rectification blade cascade is located at the front end of the upper surface of the zigzag-shroud, and an angle exists between the labyrinth seal and the rectification blade cascade. The rectification blade cascade structure is introduced to the zigzag-shroud of the rotor vane, a more effective tip shroud sealing structure for the rotor vane is formed by the adoption of the rectification blade cascade and the labyrinth seal, the air leakage amount of the tip shroud of the rotor vane is largely reduced, the rotor efficiency of an aero-engine is improved, the utilization rate of fuel oil is improved, the consumption rate of fuel oil is reduced, and the engine performance and reliability of the aero-engine are improved overall.
Description
Technical field
The present invention relates to a kind of engine blade structure, be specifically related to a kind of aeroengine rotor blade sawtooth hat.
Background technique
The rotor blade sawtooth hat structure that current aeroengine extensively adopts generally coordinates with the honeycomb on stator casing, rotor blade integral shroud leakage air is sealed, to reduce air leakage rate, saw tooth structure can absorb the vibrational energy of blade simultaneously, increases blade strength.Rotor blade sawtooth hat is generally applied on Low Pressure Turbine Rotor.Because conventional rotors blade sawtooth hat only has 2 to 3 roads to obturage comb tooth (see accompanying drawing 4), sealing effect is bad, making part High Temperature High Pressure air without having utilized with regard to leakage loss (see accompanying drawing 5), reducing gas compressor/turbine efficiency, adding oil consumption rate; Also there is the total gas bounce effect defect of comb tooth class formation of obturaging in sawtooth hat, forms pneumatic excitation force, cause aeroengine complete machine oscillation.
Summary of the invention
The object of this invention is to provide a kind of aeroengine rotor blade sawtooth hat, carry out flow path direction at conventional rotors blade sawtooth hat air-flow and increase rectification leaf grating, reduce the gentle bounce effect of integral shroud air leakage rate of rotor blade, and then promote aeroengine overall performance and reliability.
Technological scheme of the present invention is:
A kind of aeroengine rotor blade sawtooth hat, this sawtooth hat is positioned at the upper end of rotor blade, sawtooth is labeled surface and is arranged obturage comb tooth and rectification leaf grating, comb tooth of obturaging is positioned at the rear end that sawtooth labels surface, rectification leaf grating is positioned at the front end that sawtooth labels surface, obturages between comb tooth and rectification leaf grating and has several angle.
Described aeroengine rotor blade sawtooth hat, its preferred version is, described rectification leaf grating quantity is 4-6.
Described aeroengine rotor blade sawtooth hat, its preferred version is, described rectification leaf grating is crescent.
Described aeroengine rotor blade sawtooth hat, its preferred version is, the direction that described rectification leaf grating is arranged is identical, and between described rectification leaf grating, interval is even.
Described aeroengine rotor blade sawtooth hat, its preferred version is, described in comb number of teeth amount of obturaging be 2-3.
Described aeroengine rotor blade sawtooth hat, its preferred version is, described in comb tooth of obturaging be arranged in parallel.
Working principle of the present invention: with the novel rotor blade of aeroengine rotor blade sawtooth of the present invention hat after aeroengine installation, the air-flow rectification leaf grating that flow path direction forms a circle-shaped entirety is carried out at rotor blade integral shroud air-flow, flow between the honeycomb of air-flow on stator casing and rectification leaf grating, the effect of rectification leaf grating is that the leakage air of flow path direction in the future becomes hoop swirling eddy by axial lead, form one gas wall, form the barrier that first stops the leakage stream of rotor blade integral shroud place air-flow, postpone the flow leakage time, reduce air-flow unit time leakage rate.By the rectification of rectification leaf grating, hoop air-flow is effectively all pressed, and greatly reduces the pneumatic excitation force caused because hoop stream pressure is uneven, alleviates gas bounce effect, thus reduces the global vibration of engine fault because rotor blade integral shroud gas bounce effect causes.After over commutation leaf grating, still have partial air to flow backward, therefore after rectification leaf grating, still retain two, three roads to obturage comb tooth, form second barrier to leakage air further, through twice barrier, rotor blade integral shroud flow leakage amount can obviously decline.
Beneficial effect of the present invention: rectification cascade structure is introduced rotor blade sawtooth hat by the present invention, rectification leaf grating and comb toothing of obturaging is adopted to form more effective rotor blade integral shroud seal structure, greatly can reduce rotor blade integral shroud air leakage rate, improve aeroengine rotor efficiency, strengthen fuel oil utilization ratio, reduce fuel consumption rate, improve overall performance and the reliability of aeroengine on the whole.
Accompanying drawing explanation
Fig. 1 is rotor blade structure schematic diagram;
Fig. 2 is rotor blade sawtooth hat plan view;
Fig. 3 is that air-flow labels nowed forming schematic diagram at rotor blade sawtooth;
Fig. 4 is conventional rotors blade structure schematic diagram;
Fig. 5 is that air-flow labels nowed forming schematic diagram at conventional rotors blade sawtooth;
In figure: 1 is sawtooth hat, and 2 is comb tooth of obturaging, and 3 is rectification leaf grating, and 4 is rotor blade, and 5 is the honeycomb on stator casing.
Embodiment
As Fig. 1, shown in 2, a kind of aeroengine rotor blade sawtooth hat, this sawtooth hat 1 is positioned at the upper end of rotor blade 4, sawtooth is preced with 1 upper surface and is arranged two obturage comb tooth 2 and five rectification leaf gratings 3, wherein four rectification leaf gratings 3 are integrated, one of them rectification leaf grating 3 is split, lay respectively at the two ends, left and right that sawtooth is preced with 1 upper surface, comb tooth 2 of obturaging is set in parallel in the rear end that sawtooth is preced with 1 upper surface, rectification leaf grating 3 is positioned at the front end that sawtooth is preced with 1 upper surface, rectification leaf grating 3 is crescent, the direction that rectification leaf grating 3 is arranged is identical, between rectification leaf grating 3, interval is even, obturage between comb tooth 2 and rectification leaf grating 3 and there is several angle.
As shown in Figure 3, during aeroengine work, first air-flow blows to the rectification leaf grating 3 of above-mentioned aeroengine rotor blade sawtooth hat 1, the leakage air of rectification leaf grating 3 flow path direction in future becomes hoop swirling eddy by axial lead, form one gas wall, form the barrier that first stops the leakage stream of rotor blade 4 blade tip air-flow, postpone the flow leakage time, reduce air-flow unit time leakage rate; By the rectification of rectification leaf grating 3, hoop air-flow is effectively all pressed, and greatly reduces the pneumatic excitation force caused because hoop stream pressure is uneven, alleviates gas bounce effect, thus reduces the global vibration of engine fault because rotor blade integral shroud gas bounce effect causes; After over commutation leaf grating 3, still have partial air to flow backward, the twice after rectification leaf grating 3 obturage comb tooth 2 further to leakage air formation second barrier, and through twice barrier, rotor blade 4 blade tip flow leakage amount can obviously decline.
High for 10cm, air mass flow are 100kg/s, pressure reduction is 2 × 105Pa before and after blade tip radial clearance 0.25mm, integral shroud Low Pressure Turbine Rotor blade 1 with the leaf of above-mentioned sawtooth hat 1 for one-level, its blade tip air leakage is 30% of conventional sawtooth hat rotor blade, and oil consumption rate can reduce 1%.With motor consumption per hour 5 tons of aviation kerosines, then per hour can saving fuel oil consumption costs=5 ton × 1%=50kg.With two the every sorties of fighter 2 hours combat duty Time Calculation, adopt the present invention can carry 200kg fuel oil less, 200kg additional load can be increased.
Claims (6)
1. an aeroengine rotor blade sawtooth hat, it is characterized in that, described sawtooth hat is positioned at the upper end of rotor blade, sawtooth is labeled surface and is arranged obturage comb tooth and rectification leaf grating, comb tooth of obturaging is positioned at the rear end that sawtooth labels surface, rectification leaf grating is positioned at the front end that sawtooth labels surface, obturages between comb tooth and rectification leaf grating and has several angle.
2. aeroengine rotor blade sawtooth hat according to claim 1, is characterized in that, described rectification leaf grating quantity is 4-6.
3. aeroengine rotor blade sawtooth hat according to claim 1 and 2, it is characterized in that, described rectification leaf grating is crescent.
4. aeroengine rotor blade sawtooth hat according to claim 3, it is characterized in that, the direction that described rectification leaf grating is arranged is identical, and between described rectification leaf grating, interval is even.
5. aeroengine rotor blade sawtooth according to claim 1 hat, is characterized in that, described in comb number of teeth amount of obturaging be 2-3.
6. aeroengine rotor blade sawtooth according to claim 5 hat, is characterized in that, described in comb tooth of obturaging be arranged in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410624101.6A CN104454026A (en) | 2014-11-09 | 2014-11-09 | Zigzag-shroud of aero-engine rotor vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410624101.6A CN104454026A (en) | 2014-11-09 | 2014-11-09 | Zigzag-shroud of aero-engine rotor vane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104454026A true CN104454026A (en) | 2015-03-25 |
Family
ID=52900696
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410624101.6A Pending CN104454026A (en) | 2014-11-09 | 2014-11-09 | Zigzag-shroud of aero-engine rotor vane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104454026A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104847416A (en) * | 2015-04-09 | 2015-08-19 | 上海理工大学 | Impeller top surrounding band and turbine |
| CN108868896A (en) * | 2018-06-29 | 2018-11-23 | 北京驰宇空天技术发展有限公司 | A kind of engine turbine moving blades and turbogenerator |
| CN110701102A (en) * | 2019-09-29 | 2020-01-17 | 中国航发沈阳发动机研究所 | Engine fan rotor with fan rotor blade structure pole provided with same |
| CN114320487A (en) * | 2022-01-07 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Grate tooth sealing structure and method suitable for same |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2110767A (en) * | 1981-11-27 | 1983-06-22 | Rolls Royce | A shrouded rotor for a gas turbine engine |
| CN101117897A (en) * | 2006-08-03 | 2008-02-06 | 通用电气公司 | Turbine blade tip shroud |
| CN101482029A (en) * | 2008-01-10 | 2009-07-15 | 通用电气公司 | Turbine blade tip shroud |
| JP2009162206A (en) * | 2008-01-10 | 2009-07-23 | Hitachi Ltd | Turbine rotor blade |
| CN201650377U (en) * | 2010-05-19 | 2010-11-24 | 中国航空动力机械研究所 | Blade with crest |
| CN101956573A (en) * | 2009-07-17 | 2011-01-26 | 通用电气公司 | The turbine bucket tip lid of perforation |
| CN103291376A (en) * | 2012-03-01 | 2013-09-11 | 通用电气公司 | Rotating turbomachine component with tip leakage flow guide |
-
2014
- 2014-11-09 CN CN201410624101.6A patent/CN104454026A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2110767A (en) * | 1981-11-27 | 1983-06-22 | Rolls Royce | A shrouded rotor for a gas turbine engine |
| CN101117897A (en) * | 2006-08-03 | 2008-02-06 | 通用电气公司 | Turbine blade tip shroud |
| CN101482029A (en) * | 2008-01-10 | 2009-07-15 | 通用电气公司 | Turbine blade tip shroud |
| JP2009162206A (en) * | 2008-01-10 | 2009-07-23 | Hitachi Ltd | Turbine rotor blade |
| CN101956573A (en) * | 2009-07-17 | 2011-01-26 | 通用电气公司 | The turbine bucket tip lid of perforation |
| CN201650377U (en) * | 2010-05-19 | 2010-11-24 | 中国航空动力机械研究所 | Blade with crest |
| CN103291376A (en) * | 2012-03-01 | 2013-09-11 | 通用电气公司 | Rotating turbomachine component with tip leakage flow guide |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104847416A (en) * | 2015-04-09 | 2015-08-19 | 上海理工大学 | Impeller top surrounding band and turbine |
| CN108868896A (en) * | 2018-06-29 | 2018-11-23 | 北京驰宇空天技术发展有限公司 | A kind of engine turbine moving blades and turbogenerator |
| CN110701102A (en) * | 2019-09-29 | 2020-01-17 | 中国航发沈阳发动机研究所 | Engine fan rotor with fan rotor blade structure pole provided with same |
| CN114320487A (en) * | 2022-01-07 | 2022-04-12 | 中国航发贵阳发动机设计研究所 | Grate tooth sealing structure and method suitable for same |
| CN114320487B (en) * | 2022-01-07 | 2024-07-05 | 中国航发贵阳发动机设计研究所 | Caster tooth sealing structure and method suitable for same |
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Application publication date: 20150325 |