CN108019242B - Aero-engine tip clearance active control device based on shape-memory alloy wire - Google Patents
Aero-engine tip clearance active control device based on shape-memory alloy wire Download PDFInfo
- Publication number
- CN108019242B CN108019242B CN201711348615.3A CN201711348615A CN108019242B CN 108019242 B CN108019242 B CN 108019242B CN 201711348615 A CN201711348615 A CN 201711348615A CN 108019242 B CN108019242 B CN 108019242B
- Authority
- CN
- China
- Prior art keywords
- encapsulation
- operating stick
- aero
- tip clearance
- alloy wire
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
Abstract
The present invention provides a kind of aero-engine tip clearance active control device based on shape-memory alloy wire, by encapsulation, electrode plate, insulating layer, pre-stretching memorial alloy tow, operating stick, limited roller, baffle, the composition such as spring, outer casing and interior casing；Electrode plate, pre-stretching marmem beam, operating stick, baffle and spring constitute main tip clearance control assembly；Wherein the holdings such as encapsulation, electrode plate, insulating layer, operating stick, baffle and spring are coaxial and connect support with outer casing by encapsulation, and it is vertical with above structure axis that operating stick with interior casing connect limited roller；The present invention utilizes this characteristic of temperature control shape memory metal shape memory effect, pre-stretching shape-memory alloy wire is connected on aero-engine tip clearance acting device, using suitable electric current heating that it is made to generate restoring force to it drives acting device to move up, tip clearance is quickly adjusted, realizes the active control of aero-engine tip clearance.
Description
Technical field
The present invention provides a kind of aero-engine tip clearance active control device based on shape-memory alloy wire, more really
Say it is a kind of shape memory effect realization aero-engine tip clearance active control by shape-memory alloy wire with cutting
Novel control device belongs to aero-engine control field.
Technical background
Rotor-stator system is aero-engine core component, and when work is more by mechanical load, aerodynamic loading, thermal force etc.
Field load effect, working environment are very severe.Deformation and vibration such as structure is excessive, will lead to that turn stator relative displacement be more than two
The installation gap of person, turning stator can collide and rub, that is, turn stator impact-rub malfunction.Revolving speed when due to aero-engine work
It is high, once impact-rub malfunction, which occurs, will lead to major accident, or even endanger flight safety.To avoid such accident from occurring, existing rank
The most engines of section can only for blade and casing, there are sufficiently large gap nargin in the design, but the following consequence is whirlpool
Wheel and overall efficiency significantly reduce, and fuel consumption rate increases, NOx, CO and CO2Equal noxious gas emissions increase, engine exhaust
Temperature increases to which engine life reduces.Therefore, various gap control technology especially active clearance control technologies are considered as
The key technology of aero-engine, domestic and international aero-engine research and design organization investment vast resources study it.
So far, existing active clearance control method response speed is slow, and cannot eliminate and touch when turning stator and touching and rub and occur
It rubs failure.
A kind of aero-engine tip clearance active control device based on shape-memory alloy wire proposed by the present invention, benefit
With the shape memory effect of shape-memory alloy wire, it is heated after large deformation recovery capacity and fast response characteristic, devise one
Kind of tip clearance regulating device can be realized and turn stator gap to aero-engine and quickly control, well solved
State problem.
Summary of the invention
1, the purpose of the present invention
Severe for aero-engine rotor-stator system working environment, the large deformation that structure generates, which will lead to, to be turned stator and touches to rub
The problem of failure occurs, proposes a kind of aero-engine tip clearance active control device based on shape-memory alloy wire.
The device is using the restoring force that there is the temperature control shape-memory alloy wire of pre- stretching strain to generate in electric current heating process and quickly
Response characteristic, the movement of driving operating bar realize the active control to aero-engine tip clearance to control tip clearance size.
2, technical solution
A kind of aero-engine tip clearance active control device based on shape-memory alloy wire of the present invention, by encapsulating,
Electrode plate, insulating layer, pre-stretching memorial alloy tow, operating stick, limited roller, baffle, the groups such as spring, outer casing and interior casing
At；Relationship between them is: electrode plate, pre-stretching marmem beam, operating stick, baffle and spring constitute main blade tip
Gap control assembly；Wherein the holdings such as encapsulation, electrode plate, insulating layer, operating stick, baffle and spring are coaxial and by encapsulation and outside
Casing connection support, it is vertical with above structure axis that operating stick with interior casing connect limited roller.
The encapsulation, construction is a hollow cylinder, and two auricles are welded in the two sides of the bottom of the hollow cylinder；It makes
It is processed with high temperature alloy pipe；This is in the encapsulation of hollow cylinder, and inside and outside diameter size is respectively 70mm and 76mm, a height of
150mm；The auricle of the two sides of the bottom of the encapsulation, length are respectively 10mm, 10mm, 2mm；Two auricle of bottom of the encapsulation
It is joined with bolts with outer casing, top sealing；
There are two the electrode plates, is processed using high-temperature alloy sheet material；The electrode plate is in round pie, and diameter 40mm is thick
3mm；It is 1-2mm circular through hole that several diameters are beaten on the electrode plate, and the upper and lower surface of two electrode plates passes through bolt and operation
It bar, encapsulation and is connect with memorial alloy tow both ends；
The insulating layer is arranged in two electrode plates and operating stick and encapsulation junction；
The pre-stretching shape-memory alloy wire beam has shape memory effect and handles by pre-stretching；
The operating stick is the solid cylinder structure that high-temperature alloy material is processed into, and baffle is welded with it；Operating stick will be electric
Pole plate and interior casing connect；
The limited roller is the hollow cylinder structure that high-temperature alloy material is processed into, and top is embedded with an idler wheel；In cylinder
Outer diameter is respectively 10mm and 12mm, a length of 30mm；Solid idler wheel outer diameter is 6mm, with a thickness of 2mm；It and operating stick pass through screw thread
Connection, every 120 ° of arrangements, one limited roller in operating stick, totally three form a circle.
The spring is the cylinder pressure spring that high temperature alloy is processed into, line footpath 1.5mm, a height of 25mm, internal diameter 28mm；It is fixed
Between baffle and outer casing；
The outer casing and interior casing refer to the inside and outside case structure of aero-engine double-layered case.
The present invention utilizes this characteristic of temperature control shape memory metal shape memory effect, will be pre-stretched shape-memory alloy wire
It is connected on aero-engine tip clearance acting device, uses suitable electric current heating that it is made to generate the movement of restoring force band to it
Dynamic device moves up, and quickly adjusts tip clearance, realizes the active control of aero-engine tip clearance.
3, the invention has the advantages that:
(1) the configuration of the present invention is simple carries out gap control using memory alloy material own material properties, does not need more
Complicated power device；
(2) the tip clearance regulating device power to weight ratio that designs of the present invention is big, pollution-free and noise when work, driving voltage
It is low；
(3) control device that the present invention designs can be with the size of precisely controlling displacement quantity, and is enable to respond quickly elimination
Impact-rub malfunction is conducive to the safety for improving complete machine.
Detailed description of the invention
Fig. 1 is aero-engine tip clearance active control device schematic diagram of the present invention.
Fig. 2 is aero-engine tip clearance active control device encapsulation axis side view of the present invention.
Fig. 3 is aero-engine tip clearance active control device electrode plate axis side view of the present invention.
Fig. 4 is temperature control shape memory metal shape memory effect macroscopic view schematic diagram of the present invention.
Fig. 5 is aero-engine tip clearance active control device work flow diagram of the present invention.
Fig. 6 is aero-engine tip clearance active control device limited roller master of the present invention, left view.
Fig. 6 a is aero-engine tip clearance active control device limited roller main view of the present invention.
Fig. 6 b is aero-engine tip clearance active control device limited roller left view of the present invention.
Serial number, symbol, code name are described as follows in figure:
1 is encapsulation, and 2 be electrode plate, and 3 be insulating layer, and 4 be pre-stretching shape-memory alloy wire beam, and 5 be operating stick, and 6 are limited
Position idler wheel, 7 be baffle, and 8 be spring, and 9 be outer casing, and 10 be interior casing；
11 be encapsulation hollow cylinder, and 12 be encapsulation auricle；
13 circular through holes, 14 be bolt thread hole；
15 be limit roller devices idler wheel, and 16 be limit roller devices cylinder, and 17 be limited roller external screw thread.
Specific embodiment
The present invention is illustrated with reference to the accompanying drawings and detailed description.
The structure of the embodiment of the present invention is as shown in Figure 1.Device is by encapsulation 1, electrode plate 2, insulating layer 3, pre-stretching shape note
Recall the composition such as alloy tow 4, operating stick 5, limited roller 6, baffle 7, spring 8, outer casing 9 and interior casing 10.Between them
Relationship is: electrode plate 2, pre-stretching memorial alloy beam 4, operating stick 5, baffle 7 and spring 8 constitute main tip clearance control group
Part；Wherein the holdings such as encapsulation 1, electrode plate 2, insulating layer 3, operating stick 5, baffle 7 and spring 8 are coaxial and pass through encapsulation 1 and outer machine
The connection support of casket 9, it is vertical with above structure axis that operating stick 5 with interior casing 10 connect limited roller 6.
The encapsulation 1, as shown in Figure 2.Its shape design is an encapsulation hollow cylinder 11, the two sides of the bottom weldering of the cylinder 11
Connect two encapsulation auricles 12.It is processed using nickel based tubular product made from high temperature alloy, the internal-and external diameter size of the cylinder 11 be respectively 70mm and
76mm, a height of 150mm；The length, width and height of the encapsulation auricle 12 are respectively 10mm, 10mm, 2mm.Two auricle 12 of bottom of the encapsulation 1
It is joined with bolts with outer casing 9, top sealing.The encapsulation 1 makes internal acting device work under air-proof condition, internal
Air-flow and energized components are isolated from the outside, and guarantee that acting device works normally.
The electrode plate 2 is processed using nickel-based high-temperature alloy sheet material, is in round pie, as shown in Figure 3；Its diameter 40mm is thick
3mm；It is 1mm circular through hole 13 that several diameters are beaten on the electrode plate 2, and memorial alloy tow both ends are each passed through two electrode plates 2
Circular through hole 13, wound bolt screw rod and pass through bolt thread hole 14 after a week and tighten bolt, such memory alloy wire is just
Centre is pressed on to reach fixed purpose by electrode plate 2 and bolt head；
It is C grades of mica or glass fibre that the insulating layer 3, which selects temperature classification, is arranged in two electrode plates 2 and behaviour
Make 1 junction of bar 5 and encapsulation, electric leakage is avoided to cause the electric current being added on memorial alloy tow 4 is too small anticipation work effect is not achieved
Fruit, it is also ensured that the safety of aero-engine work；
The pre-stretching shape-memory alloy wire beam 4 chooses temperature control NiTi shape-memory alloy wire, with shape memory
Effect is become in advance as shown in figure 4, the memorial alloy sample of certain shapes is cooled to martensitic traoformation and terminates temperature or less
Shape, then sheds load, and deformation is retained；Later, deformation sample is heated to austenite phase transformation start temperature or more, tried
Sample starts to restore the shape before deformation, and when being heated to austenite phase transformation start temperature, sample restores the shape before deformation completely.
Length is 10mm by this example, and line footpath is placed in ice water for the temperature control shape-memory alloy wire beam of 0.8mm and places it in boiling after 1 minute
1 minute in water, 100 times are recycled to stablize the memorial alloy strand material characteristic；The memorial alloy tow 4 is placed in room temperature condition
Lower 2 minutes, after place it on stretching experiment platform and fixed to clamp with fixture, tensile sample makes it have suitable pre-stretching and answers
Become.
The operating stick 5 is the solid cylinder structure that is processed into of nickel base superalloy, column diameter 26mm, a height of
70mm.Baffle is welded with it, and operating stick 5 connects memorial alloy tow 4 and interior casing 10, when electric current heats memorial alloy
When tow 4 replys deformation, memorial alloy tow 4 can drive interior casing 10 to move up by operating stick 5, entire to control workflow such as
Shown in Fig. 5.
The limited roller 6 is the hollow cylinder structure that nickel base superalloy is processed into, as shown in Figure 6.Top is embedded with one
Idler wheel 15.16 inner and outer diameter of cylinder is respectively 10mm and 12mm, a length of 30mm；Solid 15 outer diameter of idler wheel is 6mm, with a thickness of 2mm.
It is connect with operating stick 5 by external screw thread 17, and every 120 ° of arrangements, one limited roller 6 in operating stick 5, totally three surround one
Circle.End is contacted with the inner wall of encapsulation 1, and limited roller 6 and the inner wall of encapsulation 1 form rolling friction when operating stick 5 moves up and down
Guarantee mobile accuracy.
The spring 8 is the cylinder pressure spring that nickel base superalloy is processed into, line footpath 1.5mm, a height of 25mm, internal diameter 28mm.
It is fixed between baffle 7 and outer casing 9, plays damping effect.
The outer casing 9 refers to the inside and outside case structure of aero-engine double-layered case with interior casing 10.
The present invention utilizes this characteristic of temperature control shape memory metal shape memory effect, will be pre-stretched shape-memory alloy wire
It is connected on aero-engine tip clearance acting device, uses suitable electric current heating that it is made to generate the movement of restoring force band to it
Dynamic device moves up, and quickly adjusts tip clearance, realizes the active control of aero-engine tip clearance.
Claims (5)
1. a kind of aero-engine tip clearance active control device based on pre-stretching shape-memory alloy wire beam, feature exist
In: by encapsulation, electrode plate, insulating layer, pre-stretching shape-memory alloy wire beam, operating stick, limited roller, baffle and groups of springs
At；Relationship between them is: electrode plate, pre-stretching shape-memory alloy wire beam, operating stick, baffle and spring are constituted between blade tip
Gap control assembly；Wherein encapsulation, electrode plate, insulating layer, operating stick, baffle and spring keep coaxial and by encapsulation and outer casing
Connection support, limited roller are vertical with above-mentioned axle of spring；
The encapsulation, construction is a hollow cylinder, and the two sides of the bottom of the hollow cylinder are welded with auricle；It uses high
Temperature alloy tubular object extruding；Two auricle of bottom and the outer casing of the encapsulation are joined with bolts, top sealing；
There are two the electrode plates, is processed using high-temperature alloy sheet material；The electrode plate be in round pie, two electrode plates by bolt,
Operating stick and encapsulation are connect with pre-stretching shape-memory alloy wire beam both ends；
The insulating layer is arranged in electrode plate and operating stick and encapsulation junction；
The pre-stretching shape-memory alloy wire beam has shape memory effect and handles by pre-stretching；
The operating stick is the solid cylinder structure that high-temperature alloy material is processed into, and baffle is welded with it；Operating stick is by electrode plate
It is connected with interior casing；
The spring is the cylinder pressure spring that high temperature alloy is processed into, it is fixed between baffle and outer casing；
The top of the hollow cylinder structure that there is the limited roller high-temperature alloy material to be processed into, hollow cylinder structure is embedded with one
Idler wheel；Limited roller is connected through a screw thread with operating stick, and every 120 ° of arrangements, one limited roller in operating stick, totally three are enclosed
At a circle.
2. a kind of aero-engine tip clearance master based on pre-stretching shape-memory alloy wire beam according to claim 1
Dynamic control device, it is characterised in that: the inside and outside diameter size of the encapsulation is respectively 70mm and 76mm, a height of 150mm；It is described hollow
The length of cylinder bottom two sides auricle is respectively 10mm, 10mm, 2mm.
3. a kind of aero-engine tip clearance master based on pre-stretching shape-memory alloy wire beam according to claim 1
Dynamic control device, it is characterised in that: should be in the electrode plate of round pie, diameter 40mm, thick 3mm；It is beaten on the electrode plate predetermined
A diameter is 1-2mm round thread hole.
4. a kind of aero-engine tip clearance master based on pre-stretching shape-memory alloy wire beam according to claim 1
Dynamic control device, it is characterised in that: the spring, line footpath 1.5mm, a height of 25mm, internal diameter 28mm.
5. a kind of aero-engine tip clearance master based on pre-stretching shape-memory alloy wire beam according to claim 1
Dynamic control device, it is characterised in that: its cylinder internal-and external diameter of the limited roller is respectively 10mm and 12mm, a length of 30mm；Idler wheel
Outer diameter be 6mm, with a thickness of 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711348615.3A CN108019242B (en) | 2017-12-15 | 2017-12-15 | Aero-engine tip clearance active control device based on shape-memory alloy wire |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711348615.3A CN108019242B (en) | 2017-12-15 | 2017-12-15 | Aero-engine tip clearance active control device based on shape-memory alloy wire |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108019242A CN108019242A (en) | 2018-05-11 |
| CN108019242B true CN108019242B (en) | 2019-08-06 |
Family
ID=62073972
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711348615.3A Active CN108019242B (en) | 2017-12-15 | 2017-12-15 | Aero-engine tip clearance active control device based on shape-memory alloy wire |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108019242B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109611237B (en) * | 2018-11-30 | 2020-05-22 | 北京航空航天大学 | Memory alloy driven front duct ejector of variable cycle engine adjustable mechanism |
| CN113446069B (en) * | 2020-03-26 | 2023-06-20 | 中国航发商用航空发动机有限责任公司 | Aeroengine blade tip clearance passive control device and aeroengine |
| CN112627917A (en) * | 2020-11-16 | 2021-04-09 | 株洲丰发精工实业有限公司 | Case for aircraft engine and machining method thereof |
| CN113107615B (en) * | 2021-04-08 | 2022-08-26 | 沈阳航空航天大学 | Active clearance control labyrinth seal structure based on eccentric damping action |
| CN113090342B (en) * | 2021-04-08 | 2023-01-13 | 沈阳航空航天大学 | Active clearance control labyrinth seal structure based on memory alloy wire |
| CN113090340B (en) * | 2021-04-08 | 2023-02-14 | 沈阳航空航天大学 | Active clearance control labyrinth seal based on shape memory alloy |
| CN116291762B (en) * | 2023-04-07 | 2023-10-13 | 南京航空航天大学 | Aero-engine high-pressure turbine component with controllable blade tip clearance and aero-engine |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7367776B2 (en) * | 2005-01-26 | 2008-05-06 | General Electric Company | Turbine engine stator including shape memory alloy and clearance control method |
| CN102152017B (en) * | 2011-02-14 | 2012-10-24 | 吉林大学 | Method for connecting TiNi shape memory alloy and austenitic stainless steel heterogenetic material |
| CN102352778B (en) * | 2011-10-20 | 2013-11-27 | 西北工业大学 | Electronic mechanical actuation device for actively controlling tip clearance of turbine |
| CN105201562B (en) * | 2014-05-28 | 2017-07-04 | 中航商用航空发动机有限责任公司 | active clearance control method and system |
| CN204140141U (en) * | 2014-09-28 | 2015-02-04 | 中航商用航空发动机有限责任公司 | The actuator of ACTIVE CONTROL tip clearance and system |
| CN104314621B (en) * | 2014-10-08 | 2016-04-27 | 南京航空航天大学 | A kind of fast-response control device of the turbine blade-tip gap control system based on memory alloy |
| CN204436483U (en) * | 2015-02-04 | 2015-07-01 | 厦门大学 | A kind of turbine blade-tip gap ACTIVE CONTROL mechanism |
| CN106555619B (en) * | 2015-09-30 | 2018-07-24 | 中国航发商用航空发动机有限责任公司 | The control device and method in gas turbine blade gap |
| CN105401986B (en) * | 2015-11-30 | 2017-01-18 | 成都发动机（集团）有限公司 | Flow channel arrangement structure of aero-engine high-pressure turbine cooling air |
-
2017
- 2017-12-15 CN CN201711348615.3A patent/CN108019242B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108019242A (en) | 2018-05-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108019242B (en) | Aero-engine tip clearance active control device based on shape-memory alloy wire | |
| CN105915115A (en) | Rotary hammering-type moon-surface piezoelectric power generation device and work mode thereof | |
| CN206352344U (en) | tension and compression type damper based on magnetic control shape memory alloy | |
| CN205841114U (en) | A kind of rotation collision type lunar surface piezoelectric energy collecting device | |
| CN202578939U (en) | Hand temperature energy supply type thermo power device | |
| CN204610022U (en) | A kind of turbocharger deflation valve lid | |
| CN204289200U (en) | Adopt the 10-35 kilovolt high pressure New Type Isolating Switch of memory alloy spring | |
| CN201736827U (en) | Pantograph | |
| CN206313724U (en) | A kind of efficient open air device of solar generating of optically focused | |
| CN203906179U (en) | Lifting wing lift lever transmission type wind resistance device special for wind power generation | |
| CN201785888U (en) | Shape memory alloy self-sensing damper | |
| CN205446535U (en) | Woven wire rubber vibration isolator of variable ratio frequency changer | |
| CN205064669U (en) | Variable ratio frequency changer isolator based on super -elasticity SMA | |
| CN202940677U (en) | Novel low-temperature-rise water-cooled stator frame | |
| CN210343574U (en) | Horizontal hydroelectric generating set | |
| CN202798382U (en) | Rotor ohmic heating tooling | |
| CN107091208A (en) | A kind of active dual direction drive mechanism and application method | |
| CN207750145U (en) | A kind of piston of the passive energy storage of double acting | |
| CN207009298U (en) | A kind of weighting meter | |
| CN206655771U (en) | A kind of multi-angle tuning wind power generation plant | |
| CN204290813U (en) | A kind of efficiency power generation corridor | |
| CN205154381U (en) | Automatically controlled turbo charger | |
| CN108535039A (en) | A kind of micro- damage sampler | |
| CN203764217U (en) | Expansion device with self-protection function | |
| CN110566422A (en) | resonance power generation device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |