CN110529189A - A kind of low-pressure turbine blade sawtooth hat construction design method - Google Patents
A kind of low-pressure turbine blade sawtooth hat construction design method Download PDFInfo
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- CN110529189A CN110529189A CN201910715057.2A CN201910715057A CN110529189A CN 110529189 A CN110529189 A CN 110529189A CN 201910715057 A CN201910715057 A CN 201910715057A CN 110529189 A CN110529189 A CN 110529189A
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- Prior art keywords
- low
- pressure turbine
- turbine blade
- sawtooth
- field
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Abstract
The invention belongs to impeller machinery technical fields, are related to a kind of low-pressure turbine blade sawtooth hat construction design method, mainly for high load capacity Low Pressure Turbine Rotor blade.It determines that the step of sawtooth is preced with structure feature is as follows: establishing global coordinate system XYZ and integral shroud coordinate system X1Y1Z1；Diameter height D where giving the low-pressure turbine blade sawtooth hat field of conjugate action according to the requirement of pneumatic design, to meet engine performance requirement；Determine the angle α of low-pressure turbine blade sawtooth the hat field of conjugate action and Y-axis；Determine the pre- torsional angle △ β of low-pressure turbine blade；According to angle α, pre- torsional angle △ β and diameter height D, determine that low-pressure turbine blade sawtooth is preced with field of conjugate action chord width b.The design method realizes the torque on the low-pressure turbine blade field of conjugate action and the righting moment balance because of low-pressure turbine blade blade after rotation；At the same time, it is preced between the field of conjugate action by low-pressure turbine blade sawtooth and is mutually constrained, achieve the purpose that reduce blade amplitude.
Description
Technical field
The invention belongs to impeller machinery technical fields, are related to a kind of Turbine Sawtooth Shroud design method, negative mainly for height
Lotus Low Pressure Turbine Rotor blade.
Background technique
Core component one of of the low-pressure turbine blade as aviation gas turbine Duct-Burning Turbofan key is stablized, is reliable
Work influence aviation gas turbine Duct-Burning Turbofan using safe.
As aeropropulsion system develops to the direction of high thrust ratio, compressor pressure ratio, turbine inlet temperature and efficiency are wanted
It asks higher and higher, under identical front face area, higher want is proposed using temperature, revolving speed and efficiency to low-pressure turbine blade
It asks.Consider from aspect of performance, in low-pressure turbine blade blade tip location arrangements integral shroud, can effectively reduce at blade tip position
Stream, can effectively improve low-pressure turbine efficiency；Consider from configuration aspects, it is low due to the elongated feature of low-pressure turbine blade
Pressure turbo blade needs to arrange integral shroud to limit blade amplitude, to achieve the purpose that reduce blade root vibration stress, guarantees low pressure
The safety of turbo blade work, reliability.Existing integral shroud design is usually common imitated or goes to set according to the experience of designer
Meter, the integral shroud homogeneity designed are very poor.
Summary of the invention
The purpose of the present invention: a kind of design method of low-pressure turbine blade sawtooth hat is proposed, in the high-revolving work of high temperature
Under state, low-pressure turbine blade blade tip location arrangements sawtooth be preced with, reach improve turbo blade working efficiency, job security and
The purpose of reliability.
Technical solution of the invention: a kind of low-pressure turbine blade sawtooth hat construction design method, it is negative mainly for height
Lotus Low Pressure Turbine Rotor blade.It determines that the step of sawtooth is preced with structure feature is as follows: establishing global coordinate system XYZ and integral shroud coordinate system
X1Y1Z1；Diameter height D where giving the low-pressure turbine blade sawtooth hat field of conjugate action according to the requirement of pneumatic design, is started with meeting
Machine performance requirement；Determine the angle α of low-pressure turbine blade sawtooth the hat field of conjugate action and Y-axis；Determine the pre- torsional angle △ of low-pressure turbine blade
β；According to angle α, pre- torsional angle △ β and diameter height D, determine that low-pressure turbine blade sawtooth is preced with field of conjugate action chord width b；Determine non-engagement
Face；The non-field of conjugate action is in integral shroud coordinate system Y1Chord width on direction is designed according to the theoretical value after low-pressure turbine blade pretwist, most
Final value is that theoretical value subtracts reserved gap；Determine that sawtooth is preced with position of centre of gravity: after completing above content, analysis blade tip section is used
Property, relative position of the sawtooth hat center of gravity at blade tip is checked, under conditions of guaranteeing above-mentioned chord width, by whole translation adjustment come really
Sawtooth hat will not add biggish moment of flexure when protecting work.
Advantageous effects: when design low-pressure turbine blade sawtooth hat, by the reality between two fields of conjugate action in the Y direction
Chord width is designed as being greater than the value of theoretical chord width, and when assembling low-pressure turbine blade, due to chord width interference, sawtooth hat can revolve counterclockwise
Turn to eliminate interference and form the domain, to realize torque on the low-pressure turbine blade field of conjugate action and because of low-pressure turbine blade after rotation
The righting moment of blade balances.Above-mentioned design is preced between the field of conjugate action by low-pressure turbine blade sawtooth and is mutually constrained, and reduction is reached
The purpose of blade amplitude.
Detailed description of the invention
Fig. 1 is zigzag integral shroud design parameter schematic diagram,
Fig. 2 is zigzag integral shroud position view in blade.
Specific embodiment
The present invention is described in further details below.
The construction design method of low-pressure turbine blade sawtooth hat, the main relevant parameters being related to have: defining following parameter；Saw
Diameter height D, the sawtooth hat field of conjugate action and Y-direction angle α where any given point Q of the crown field of conjugate action, the pre- torsional angle △ β of sawtooth hat and
Sawtooth is preced with field of conjugate action chord width b, the specific steps are as follows:
1, global coordinate system XYZ: using blade centre of gyration line direction as X-axis, to pass through blade tenon center, and normal direction side
Intersection point to plane and X-axis for X-direction is coordinate origin, and being directed toward blade exhaust edge direction is positive direction, to cross origin simultaneously
Straight line perpendicular to X-axis is Y-axis, and positive direction is directed toward blade basin to Z axis is determined according to the right-hand rule；
2, integral shroud coordinate system X1Y1Z1: centered on global coordinate system origin, using global coordinate system Z axis negative direction as axis,
The coordinate system that rotation △ β angle obtains；
3, the hot runner height given according to pneumatic design determines that cold conditions Low Pressure Turbine Rotor blade sawtooth is preced with the field of conjugate action
Diameter D where set point Q；
4, the sawtooth hat field of conjugate action and Y-direction angle α OK range are determined: when α is greater than angle [alpha]2When, tightness is small, the field of conjugate action
Between normal pressure variation acutely, integral shroud unstable working condition even the field of conjugate action there is gap；Meanwhile the tolerance of vane manufacturing is objective
In the presence of field of conjugate action pressure oscillating amount caused by chord width slightly changes is big, and enchancement factor influences big；When α is less than angle [alpha]1When, to protect
The positive pressure force request for demonstrate,proving the field of conjugate action, needs biggish pretwist △ β, changing of the relative positions wear block, while the additional stress introduced by pretwist △ β
Greatly, blade exhaust side is easy to appear crackle；
Wherein, α2、α1It is empirical value.
5, determine pre- torsional angle △ β: low-pressure turbine blade bears the very big centrifugal force introduced by rotation, to guarantee low-pressure turbine
The reliability of blade blade working in working condition, should not be too big by the shearing force that sawtooth hat pretwist introduces, and prevents blade work
When making state, the lesser exhaust side trailing edge of size is cracked because being sheared nearby.
6, determine that sawtooth is preced with field of conjugate action chord width b: the angle to guarantee that sawtooth is preced with field of conjugate action working condition and Y-axis is (α+△
β) angle needs to give specific chord width b, guarantees designing desired value with Y-direction angle when sawtooth hat field of conjugate action work.
7, determine the non-field of conjugate action 1: for the non-field of conjugate action 1 because complete envelope blade tip is vented side, adjacent low-pressure turbine blade two is non-
The field of conjugate action does not contact, and there are small―gap sutures when working condition；
8, determine that sawtooth is preced with position of centre of gravity: sawtooth hat center of gravity present position will not generate excessive additional bending moment, Yi Mianzeng
Add working stress at low-pressure turbine blade blade back lateral lobe point middle part or leaf basin lateral lobe point inlet and outlet side.
In step 5, the determination method of pre- torsional angle △ β is realized by following steps: passing through the sunykatuib analysis of ANSYS software first
The normal pressure and trailing edge equivalent stress of a series of corresponding field of conjugate action of pre- torsional angle △ β is calculated, then according to the lasting of blade
Life requirements and positive pressure force request choose suitable pre- torsional angle △ β.
The set point Q is in field of conjugate action intermediate region；The positive pressure force request is 10-20MPa；The diameter height D
It is given by pneumatic design.The angle α, pre- torsional angle △ β analyze to obtain its optimal angle value by Ansys software.
Embodiment
1, global coordinate system XYZ is established: using blade centre of gyration line direction as X-axis, to pass through blade tenon center, and method
Intersection point to plane and X-axis that direction is X-direction is coordinate origin, and being directed toward blade exhaust edge direction is positive direction, with excessively former
It puts and is Y-axis perpendicular to the straight line of X-axis, positive direction is directed toward blade basin to Z axis is determined according to the right-hand rule；
2, integral shroud coordinate system X is established1Y1Z1: centered on global coordinate system origin, it is with global coordinate system Z axis negative direction
Axis, the coordinate system that rotation △ β angle obtains；
3, the hot runner height given according to pneumatic design, the diameter for calculating low-pressure turbine disk and low-pressure turbine blade are stretched
Long amount, blade plane M is apart from engine axis height H when determining cold conditions.The field of conjugate action 1 is parallel with plane A, the field of conjugate action 2 and plane A
There are angles, determine distance H1 of the point Q to plane, diameter height D where calculating point Q according to H and H1；
4, determine the sawtooth hat field of conjugate action and Y-direction angle α OK range: field of conjugate action angle α is independent variable, when α is excessive
When, sawtooth is preced with the variation of field of conjugate action normal pressure acutely, is unfavorable for the holding of integral shroud operating attitude；When α is too small, need biggish pre-
Torsional angle △ β is preced with use experience according to sawtooth, and α angle OK range is α1< α < α2；
5, determine pre- torsional angle △ β: low-pressure turbine blade bears the centrifugal force introduced by rotation, to guarantee low-pressure turbine blade
The reliability of blade working in working condition, should not be too big by the shearing force that sawtooth hat pretwist introduces, and prevents blade working shape
When state, the lesser exhaust side trailing edge of size is cracked because being sheared nearby.When blade trailing edge equivalent stress is larger, angle
α takes the value bigger than normal in above-mentioned 4th article of range；
6, sawtooth hat field of conjugate action chord width b: chord width b diameter height D, field of conjugate action angle α where blade quantity, point Q are determined
With the comprehensive determination of pre- torsional angle △ β, when guaranteeing sawtooth hat field of conjugate action work and Y-direction angle is in design desired value.
Wherein, blade quantity is given by pneumatic design；
7, determine the non-field of conjugate action 1: the non-field of conjugate action 1 is in the chord width on the direction Y1 according to the theory after low-pressure turbine blade pretwist
Value designs, and end value is that theoretical value subtracts reserved gap；
8, it determines that sawtooth is preced with position of centre of gravity: after completing above content, analyzing blade tip section inertia, check that sawtooth hat center of gravity exists
It relative position at blade tip will not come sawtooth hat when ensuring work by whole translation adjustment under conditions of guaranteeing above-mentioned chord width
Add biggish moment of flexure.
Claims (9)
1. a kind of low-pressure turbine blade sawtooth is preced with construction design method, which is characterized in that the design method comprises the following steps that
The first step establishes global coordinate system XYZ and integral shroud coordinate system X1Y1Z1；
Second step determines the hat engagement of cold conditions Low Pressure Turbine Rotor blade sawtooth according to the hot runner height that pneumatic design gives
Diameter D where any given point Q in face；
Third step determines the angle α of low-pressure turbine blade sawtooth the hat field of conjugate action and Y-axis；
4th step determines the pre- torsional angle △ β of low-pressure turbine blade；
5th step determines that low-pressure turbine blade sawtooth is preced with field of conjugate action chord width b according to angle α, pre- torsional angle △ β and diameter height D；
6th step determines the non-field of conjugate action；Because complete envelope blade tip is vented side, adjacent low-pressure turbine blade two is non-to be nibbled the non-field of conjugate action
Conjunction face does not contact, and guarantees that there are small―gap sutures when working condition；
7th step determines that sawtooth is preced with position of centre of gravity.
2. low-pressure turbine blade sawtooth according to claim 1 is preced with construction design method, which is characterized in that the global seat
Mark system XYZ: using blade centre of gyration line direction as X-axis, to pass through blade tenon center, and normal orientation is the flat of X-direction
The intersection point of face and X-axis is coordinate origin, and being directed toward blade exhaust edge direction is positive direction, to cross origin and perpendicular to the straight line of X-axis
For Y-axis, positive direction is directed toward blade basin to Z axis is determined according to the right-hand rule.
3. low-pressure turbine blade sawtooth according to claim 1 is preced with construction design method, which is characterized in that the integral shroud is sat
Mark system X1Y1Z1: centered on global coordinate system XYZ origin, using global coordinate system Z axis negative direction as axis, rotation △ β angle is obtained
The coordinate system arrived.
4. low-pressure turbine blade sawtooth according to claim 1 is preced with construction design method, which is characterized in that the fixed point Q
In field of conjugate action intermediate region.
5. low-pressure turbine blade sawtooth according to claim 1 is preced with construction design method, which is characterized in that in third step,
The method for determining the angle α of the low-pressure turbine blade sawtooth hat field of conjugate action and Y-axis is as follows: when α is greater than angle [alpha] 2, tightness is small,
Acutely, there is gap in the integral shroud unstable working condition even field of conjugate action for normal pressure variation between the field of conjugate action；Meanwhile the public affairs of vane manufacturing
Poor objective reality, field of conjugate action pressure oscillating amount caused by chord width slightly changes is big, and enchancement factor influences big；When α is less than angle [alpha] 1
When, for the positive pressure force request for guaranteeing the field of conjugate action, biggish pretwist △ β, changing of the relative positions wear block are needed, while being introduced by pretwist △ β
Additional stress is big, and blade exhaust side is easy to appear crackle；It is preced with use experience according to sawtooth, α angle OK range is α1< α < α2；
Wherein, α 2, α 1 are empirical value.
6. low-pressure turbine blade sawtooth according to claim 1 is preced with construction design method, which is characterized in that in the 4th step,
Determine pre- torsional angle △ β method are as follows: low-pressure turbine blade bears the centrifugal force introduced by rotation, to guarantee low-pressure turbine blade in work
The reliability for making blade working when state, should not be too big by the shearing force that sawtooth hat pretwist introduces, when preventing blade working state,
The lesser exhaust side trailing edge of size is cracked because being sheared nearby, designs a model and analyzes to obtain by software.
7. low-pressure turbine blade sawtooth according to claim 1 is preced with construction design method, which is characterized in that the 5th step determines
Sawtooth hat field of conjugate action chord width b: chord width b diameter height D, field of conjugate action angle α and pre- torsional angle △ β where blade quantity, point Q is comprehensive
It determines, with Y-direction angle in design desired value when guaranteeing sawtooth hat field of conjugate action work.
8. low-pressure turbine blade sawtooth according to claim 7 is preced with construction design method, which is characterized in that blade quantity by
Pneumatic design is given.
9. according to claim 1, low-pressure turbine blade sawtooth described in 5 or 6 is preced with construction design method, which is characterized in that angle
α, pre- torsional angle △ β analyze to obtain its optimal angle value by Ansys software.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114233399A (en) * | 2022-02-23 | 2022-03-25 | 成都中科翼能科技有限公司 | Method for controlling contact stress of turbine rotor blade shroud contact surface |
| CN115099052A (en) * | 2022-07-08 | 2022-09-23 | 中国航发沈阳发动机研究所 | Turbine working blade with blade shroud and pre-torsion resilience design method thereof |
| CN115688314A (en) * | 2022-11-03 | 2023-02-03 | 北京全四维动力科技有限公司 | Finite element analysis based turbine blade pre-twisting simulation design method and device |
| CN115828713A (en) * | 2023-02-22 | 2023-03-21 | 中国航发沈阳发动机研究所 | Design method of single crystal turbine blade shroud of aero-engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115099052A (en) * | 2022-07-08 | 2022-09-23 | 中国航发沈阳发动机研究所 | Turbine working blade with blade shroud and pre-torsion resilience design method thereof |
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| CN115828713A (en) * | 2023-02-22 | 2023-03-21 | 中国航发沈阳发动机研究所 | Design method of single crystal turbine blade shroud of aero-engine |
| CN115828713B (en) * | 2023-02-22 | 2023-04-18 | 中国航发沈阳发动机研究所 | Design method of single crystal turbine blade shroud of aircraft engine |
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Application publication date: 20191203 |