CN104612758A - Low-pressure turbine blade with low loss - Google Patents
Low-pressure turbine blade with low loss Download PDFInfo
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- CN104612758A CN104612758A CN201410798306.6A CN201410798306A CN104612758A CN 104612758 A CN104612758 A CN 104612758A CN 201410798306 A CN201410798306 A CN 201410798306A CN 104612758 A CN104612758 A CN 104612758A
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Abstract
The invention provides a low-pressure turbine blade with a low loss. According to the low-pressure turbine blade, an original low-pressure turbine blade is divided into a blade root end region, a blade tip end region and a two-dimensional flowing region in the blade height direction; meanwhile wave-shaped cutting is conducted on the front edge of the turbine blade so that a plurality of saw teeth can be formed on the front edge portion, 3% axial chord length elongation is conducted on the original low-pressure turbine blade so as to make up for the defect that the power capacity of the cut blade profile is lowered, and elongation is conducted through arc front edge points in the blade in the middle arc tangent line direction. According to the low-pressure turbine blade with the low loss, improvement is conducted on the front edge of the original low-pressure turbine blade, so that two-dimensional flowing region separation is inhibited originally while the extra loss caused by the high-Re-state wave-shaped front edge is lowered, the application range of the passive control scheme is broadened, and the control scheme can conduct effective control over end region three-dimensional separation.
Description
Technical field
The invention belongs to civil aviation technical field, particularly relate to a kind of low-pressure turbine blade of low loss.
Background technique
Current, because large Bypass Ratio Turbofan Engine has outstanding oil consumption rate and thrust performance, because being widely used in civil aviation field.The thrust of this motor 90% comes from fan, and this just causes the low-pressure turbine progression of drive fan more, and usual low-pressure turbine weight can account for 20% ~ 30% of whole motor.And to reduce low-pressure turbine weight be one of effective way of motor loss of weight, also can improve engine thrust-weight ratio simultaneously, reduce and manufacture and operation maintenance cost.The more loss of weight scheme of current research is that the load by improving blade carries out.Highly loaded blade design is exactly the airload improving individual blade by reducing solidity of blades, thus reduces single-stage lobe numbers on the basis keeping original grade of load level.Improve blade loads, the adverse pressure gradient of runner mid-rear portion will raise to some extent, cause boundary layer on it to be easy to be separated thus.Meanwhile, this also makes the suction surface near blade trailing edge and end wall surface angular region form three-dimensional separation, and these two kinds separation all make turbine vane type loss increase.In addition, for civilian large Bypass Ratio Turbofan Engine, low-pressure turbine under its design point (cruising condition) is in low Re number working state all the time, this separation exacerbating low-pressure turbine blade suction surface boundary layer is further separated with petiolarea three-dimensional, thus significantly add profile loss, and the pneumatic efficiency of low-pressure turbine may be affected, even cause blade stall, finally cause whole motor normally to work.
The method controlled for turbine blade two dimensional separation is a lot, and wherein ACTIVE CONTROL comprises the scheme such as jet, plasma, and Passive Control comprises boss, mixes line, leading edge waveform etc.The control be separated for turbine blade petiolarea three-dimensional is also divided into initiatively and passive two kinds of modes, and wherein ACTIVE CONTROL comprises that wall is bled, the scheme such as jet, and Passive Control comprises multiple non-axis symmetry end face design etc.But do not have a kind of control mode can take into account the damage control of two aspects.
In addition, current use wave-shaped front edge controls turbine blade separation and is still in the study mechanism stage, this control program mainly by arranging the wave-shaped front edge of constant size in low-pressure turbine blade leading edge, thus reduces the two-dimentional profile loss of turbine within the scope of certain turbine.But the operation interval of this control device narrower (loss is larger when high Re), simultaneously more weak to the control effects that petiolarea large scale is separated.
Summary of the invention
Under solving the low Re of low-pressure turbine, be separated serious problem, the object of the present invention is to provide a kind of turbine blade that effectively can reduce separation losses, thus improve aeroplane engine engine efficiency.
In order to achieve the above object, the low-pressure turbine blade of low loss provided by the invention is that original low-pressure turbine blade is divided into blade root petiolarea, blade tip petiolarea and two-dimensional flow district along leaf height direction, in its leading edge, carry out waveform cutting and make leading edge position form multiple sawtooth simultaneously, and original low-pressure turbine blade is carried out to the lengthening of 3% axial chord length, to make up the decline of cutting rear blade profile acting ability, this extends through and carries out along mean camber line tangent direction in blade mean camber line leading edge point.
Described sawtooth is divided into multiple different size, in two-dimensional flow district, is wherein arranged alternately 1 type sawtooth and 2 type sawtooth, for reducing the extraneoas loss that wave leading edge under high Re number causes; At blade root petiolarea, blade tip petiolarea and two-dimensional flow district intersection arrange 3 type sawtooth; Set gradually 3 types, 4 types, 5 types to N-type sawtooth at blade root petiolarea and two-dimensional flow district intersection to blade root direction, and 3 types increase gradually to the N-type sawtooth peak-to-peak spacing of adjacent two ripple and tooth depth; Set gradually 3 types, 4 types, 5 types to N-type sawtooth at blade tip petiolarea and two-dimensional flow district intersection to blade tip direction, and 3 types increase gradually to the N-type sawtooth peak-to-peak spacing of adjacent two ripple and tooth depth.
The low-pressure turbine blade of low loss provided by the invention improves original low-pressure turbine blade leading edge, object be original suppression two-dimensional flow distinguish from while reduce the extraneoas loss that high Re state wave-shaped front edge causes, improve the Applicable scope of this Passive Control scheme, and this control program effectively can be controlled the separation of petiolarea three-dimensional, thus its Applicable scope can be expanded.
Accompanying drawing explanation
Fig. 1 is the low-pressure turbine blade structural representation of low loss provided by the invention;
Fig. 2 is the low-pressure turbine blade structure partial structure sectional view of low loss provided by the invention;
Fig. 3 is the low-pressure turbine blade structure plan view of low loss provided by the invention.
Embodiment
Be described in detail below in conjunction with the low-pressure turbine blade of the drawings and specific embodiments to low loss provided by the invention.
As shown in Fig. 1-Fig. 3, the low-pressure turbine blade of low loss provided by the invention is that original low-pressure turbine blade (1.4>=Zweifel>=1.0) is divided into blade root petiolarea A along leaf height direction, blade tip petiolarea B and two-dimensional flow district C, blade root petiolarea A, the region of blade tip petiolarea B and two-dimensional flow district C is determined by the CASCADE EXPERIMENT of original blade profile, in its leading edge, carry out waveform cutting and make leading edge position form multiple sawtooth D simultaneously, and original low-pressure turbine blade is carried out to the lengthening of 3% axial chord length, to make up the decline of cutting rear blade profile acting ability, this extends through and carries out along mean camber line tangent direction in blade mean camber line leading edge point.
Described sawtooth D is divided into multiple different size, wherein in two-dimensional flow district C, is arranged alternately 1 type sawtooth and 2 type sawtooth, for reducing the extraneoas loss that wave leading edge under high Re number causes; At blade root petiolarea A, blade tip petiolarea B and two-dimensional flow district C intersection, 3 type sawtooth are set; Set gradually 3 types, 4 types, 5 types to N-type sawtooth at blade root petiolarea A and two-dimensional flow district C intersection to blade root direction, and 3 types increase gradually to the N-type sawtooth peak-to-peak spacing of adjacent two ripple and tooth depth; Set gradually 3 types, 4 types, 5 types to N-type sawtooth at blade tip petiolarea B and two-dimensional flow district C intersection to blade tip direction, and 3 types increase gradually to the N-type sawtooth peak-to-peak spacing of adjacent two ripple and tooth depth.But in order to unduly destroy the leading edge structure of turbine blade, the yardstick of sawtooth D is unsuitable excessive.
Now the working principle of the low-pressure turbine blade of low loss provided by the invention is described below: in use, the low-pressure turbine blade of this structure flows to whirlpool a pair by being formed in the downstream of wave projection, the energy of main flow high-energy fluid is involved in boundary layer, to improve the ability that boundary layer opposing is separated.This flow direction improves the unstability of boundary layer to whirlpool in addition, impels Boundary Layer Transition in advance, makes to turn the flowing of the boundary layer after twisting and changes turbulent flow into, and then improve the resistant to separation ability of boundary layer.Meanwhile, the present invention reduces under high Re state due to extraneoas loss that leading edge moulding brings by changing the regular wave moulding in blade two-dimensional flow region.Be separated for end wall, the yardstick of separation is comparatively large, for this physical phenomenon, the present invention by improving the leading edge wave size at blade root and blade tip place, formed in the downstream of leading edge projection more large scale to whirlpool to resist petiolarea separation.
Claims (2)
1. the low-pressure turbine blade of a low loss, it is characterized in that: it original low-pressure turbine blade is divided into blade root petiolarea (A), blade tip petiolarea (B) and two-dimensional flow district (C), in its leading edge, carry out waveform cutting and make leading edge position form multiple sawtooth (D) simultaneously, and original low-pressure turbine blade is carried out to the lengthening of 3% axial chord length, to make up the decline of cutting rear blade profile acting ability, this extends through and carries out along mean camber line tangent direction in blade mean camber line leading edge point.
2. the low-pressure turbine blade of low loss according to claim 1, it is characterized in that: described sawtooth (D) is divided into multiple different size, wherein in two-dimensional flow district (C), be arranged alternately 1 type sawtooth and 2 type sawtooth, for reducing the extraneoas loss that wave leading edge under high Re number causes; At blade root petiolarea (A), blade tip petiolarea (B) and two-dimensional flow district (C) intersection arrange 3 type sawtooth; Set gradually 3 types, 4 types, 5 types to N-type sawtooth in blade root petiolarea (A) and two-dimensional flow district (C) intersection to blade root direction, and 3 types increase gradually to the N-type sawtooth peak-to-peak spacing of adjacent two ripple and tooth depth; Set gradually 3 types, 4 types, 5 types to N-type sawtooth in blade tip petiolarea (B) and two-dimensional flow district (C) intersection to blade tip direction, and 3 types increase gradually to the N-type sawtooth peak-to-peak spacing of adjacent two ripple and tooth depth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410798306.6A CN104612758A (en) | 2014-12-19 | 2014-12-19 | Low-pressure turbine blade with low loss |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410798306.6A CN104612758A (en) | 2014-12-19 | 2014-12-19 | Low-pressure turbine blade with low loss |
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| CN104612758A true CN104612758A (en) | 2015-05-13 |
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| CN201410798306.6A Pending CN104612758A (en) | 2014-12-19 | 2014-12-19 | Low-pressure turbine blade with low loss |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105626159A (en) * | 2016-03-03 | 2016-06-01 | 哈尔滨工程大学 | Variable geometry turbine with wavy concaved structures on front edges of movable blades |
| CN104985387B (en) * | 2015-05-21 | 2017-05-17 | 上海长知实业有限公司 | Integral repairing method for vane tip of vane |
| CN108019237A (en) * | 2017-11-28 | 2018-05-11 | 武汉大学 | A kind of bionical blade profile of steam turbine for suppressing flow separation |
| CN109058023A (en) * | 2018-08-17 | 2018-12-21 | 武汉大学 | Widen the method and pump turbine in pump turbine operation stability region |
| CN110985410A (en) * | 2019-12-19 | 2020-04-10 | 中国航空发动机研究院 | Transonic compressor plane cascade with bionic wavy structure leading edge |
| FR3087483A1 (en) * | 2018-10-18 | 2020-04-24 | Safran Aircraft Engines | PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT |
| CN112610513A (en) * | 2020-12-04 | 2021-04-06 | 北京航空航天大学 | Non-uniform wave-shaped front edge stationary blade and modeling method thereof |
| EP3867498B1 (en) * | 2018-10-18 | 2023-04-19 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine |
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| US20050271513A1 (en) * | 2004-06-02 | 2005-12-08 | Erik Johann | Compressor blade with reduced aerodynamic blade excitation |
| CN101716995A (en) * | 2009-10-12 | 2010-06-02 | 章成谊 | Waved wing and waved surface of object |
| CN102926818A (en) * | 2012-05-03 | 2013-02-13 | 李仕清 | High-stability and low-vibration vane, energy-gathered compound vane or efficient high-intensity engine |
| US20130164488A1 (en) * | 2011-12-22 | 2013-06-27 | General Electric Company | Airfoils for wake desensitization and method for fabricating same |
| WO2014026246A1 (en) * | 2012-08-16 | 2014-02-20 | Adelaide Research & Innovation Pty Ltd | Improved wing configuration |
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- 2014-12-19 CN CN201410798306.6A patent/CN104612758A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050271513A1 (en) * | 2004-06-02 | 2005-12-08 | Erik Johann | Compressor blade with reduced aerodynamic blade excitation |
| CN101716995A (en) * | 2009-10-12 | 2010-06-02 | 章成谊 | Waved wing and waved surface of object |
| US20130164488A1 (en) * | 2011-12-22 | 2013-06-27 | General Electric Company | Airfoils for wake desensitization and method for fabricating same |
| CN102926818A (en) * | 2012-05-03 | 2013-02-13 | 李仕清 | High-stability and low-vibration vane, energy-gathered compound vane or efficient high-intensity engine |
| WO2014026246A1 (en) * | 2012-08-16 | 2014-02-20 | Adelaide Research & Innovation Pty Ltd | Improved wing configuration |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104985387B (en) * | 2015-05-21 | 2017-05-17 | 上海长知实业有限公司 | Integral repairing method for vane tip of vane |
| CN105626159A (en) * | 2016-03-03 | 2016-06-01 | 哈尔滨工程大学 | Variable geometry turbine with wavy concaved structures on front edges of movable blades |
| CN108019237A (en) * | 2017-11-28 | 2018-05-11 | 武汉大学 | A kind of bionical blade profile of steam turbine for suppressing flow separation |
| CN109058023A (en) * | 2018-08-17 | 2018-12-21 | 武汉大学 | Widen the method and pump turbine in pump turbine operation stability region |
| FR3087483A1 (en) * | 2018-10-18 | 2020-04-24 | Safran Aircraft Engines | PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT |
| US11560796B2 (en) | 2018-10-18 | 2023-01-24 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine for an aircraft |
| EP3867498B1 (en) * | 2018-10-18 | 2023-04-19 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine |
| US11732588B2 (en) | 2018-10-18 | 2023-08-22 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine for an aircraft |
| CN110985410A (en) * | 2019-12-19 | 2020-04-10 | 中国航空发动机研究院 | Transonic compressor plane cascade with bionic wavy structure leading edge |
| CN112610513A (en) * | 2020-12-04 | 2021-04-06 | 北京航空航天大学 | Non-uniform wave-shaped front edge stationary blade and modeling method thereof |
| CN112610513B (en) * | 2020-12-04 | 2021-08-31 | 北京航空航天大学 | Non-uniform wave-shaped front edge stationary blade and modeling method thereof |
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Application publication date: 20150513 |