CN102400718A - NiTi shape memory alloy blade for deformable turbofan engine - Google Patents
NiTi shape memory alloy blade for deformable turbofan engine Download PDFInfo
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- CN102400718A CN102400718A CN2011103751969A CN201110375196A CN102400718A CN 102400718 A CN102400718 A CN 102400718A CN 2011103751969 A CN2011103751969 A CN 2011103751969A CN 201110375196 A CN201110375196 A CN 201110375196A CN 102400718 A CN102400718 A CN 102400718A
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- heating equipment
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Abstract
The invention provides a NiTi shape memory alloy blade for a deformable turbofan engine. The deformable turbofan engine consists of the NiTi shape memory alloy blade, an outer bypass duct, a ventilation heating device, a switch, an inner bypass duct and a ventilation heating device inner structure, wherein the NiTi shape memory alloy blade is positioned at the most front end of the inner structure of the turbofan engine; the left end of the ventilation heating device is positioned at the position of the NiTi shape memory alloy blade and the right end of the ventilation heating device is positioned at the position of the inner bypass duct of the engine; the switch is positioned at the left end of the ventilation heating device; the ventilation heating device inner structure is positioned at the right end of the ventilation heating device; the outer bypass duct and the inner bypass duct are arranged on the right of the NiTi shape memory alloy blade; and the outer bypass duct is positioned outside the inner bypass duct. The NiTi shape memory alloy blade has high damp, high flexibility and high recycling stability, is corrosion resistant and abrasion resistant, can be made into an engine blade and can meet requirements on stability; and by the NiTi shape memory alloy blade, a product is lighter and energy consumption is reduced.
Description
(1) technical field
The present invention relates to blade of aviation engine, is exactly a kind of deformable turbofan engine NiTi marmem blade specifically.
(2) background technique
Turbofan engine is a kind of of airplane engine, and the optimal flying speed of turbofan engine is 400 to 1000 kilometers, and therefore most now aeroengines all adopt turbofan as power resources.The part of the core air process of motor is called main duct, only has the core engine external lateral portion of fan air process to be called by-pass air duct., the thrust that the outer culvert thrust of turbofan engine comes from fan fully and produced is so fan is most important for turbofan engine.The ratio of by-pass air duct and main duct MAF is bypass ratio, under different working conditions, for the bypass ratio of motor different requirement arranged.As aircraft climb, bypass ratio reduces when acceleration and supersonic flight, near the performance of turbojet engine, to increase thrust; When taking off, strengthen bypass ratio, with the work of turbofan engine state, to reduce oil consumption rate and noise with subsonic velocity flight.Effectively the bypass ratio of change motor has very big meaning for the work of motor.In recent years, the research about variable cycle engine (VCE) was exactly the bypass ratio of being devoted to change motor in the world, but present variable cycle engine mostly is to reach the target that changes bypass ratio through changing rotation speed of the fan with the control valve.In the last few years, along with the continuous development of material technology, marmem (SMA) had obtained successful application at aerospace field.Marmem is a kind of functional metallic material, can return to the original form under certain condition, in other words; This alloy has memory capability to shape; And its memory performance is fairly good, and some still can restore to the original state after changing 5,000,000 times repeatedly under certain condition.Marmem is found in martensitic phase transformation; Usually be called parent phase (P) to the high temperature in the martensitic phase transformation mutually; Low temperature is called martensitic phase (M) mutually, and the phase transformation from the parent phase to the martensitic phase is called the positive phase transformation of martensite, and the phase transformation from the martensitic phase to the parent phase is called the martensite reverse transformation.With the cooling of high temperature parent phase, the temperature that stops to martensitic phase transformation becomes M
fWith the low-temperature martensite heat phase, martensitic phase all is converted to the state of parent phase, and this temperature is A
fSMA has very high energy density; Can not cause the remarkable increase of weight; Thereby enjoy the concern of aviation industry; Utilize the big restoring force that the memory effect of SMA provides and reply displacement greatly, make its shape that has been applied in spaceship antenna pattern, aircraft wing, engine nozzle control and in these structural vibrations controls.
(3) summary of the invention
The object of the present invention is to provide a kind of deformable turbofan engine NiTi marmem blade.
The objective of the invention is to realize like this: it is made up of NiTi marmem blade, by-pass air duct, ventilation heating equipment, switch, main duct and ventilation heating equipment internal structure; NiTi marmem blade is positioned at the turbofan engine internal structure foremost; Ventilation heating equipment left end is positioned at NiTi marmem blade place; Right-hand member is positioned at motor main duct place, and switch is positioned at the left end of ventilation heating equipment, and ventilation heating equipment internal structure is positioned at the right-hand member of ventilation heating equipment; The right of NiTi marmem blade is by-pass air duct and main duct, and by-pass air duct is positioned at the outside of main duct.The present invention also has following technical characteristics:
(1) described NiTi marmem blade has shape A and shape B, when motor needs big bypass ratio, adopts shape A, when little bypass ratio, adopts shape B, at state 1 corresponding blade profile A, at state 2 corresponding blade profile B.
(2) described ventilation heating equipment is opened switch by switch and its working state of turbine control when NiTi marmem leaf temperature need raise and keep, and turbine work just can feed hot air.
The present invention has following beneficial effect: as long as the temperature of control NiTi marmem blade just can make NiTi marmem blade under two kinds of different shapes, change; Can control bypass ratio within the specific limits through the temperature of control NiTi marmem blade according to the flight condition of aircraft; Can improve the efficient of motor greatly, practice thrift fuel oil; The NiTi marmem that the present invention adopts has high damping, corrosion-resistant, wear-resisting, and good toughness, and the good stability that uses is repeatedly done engine blade with it, can guarantee its requirement aspect stable; The NiTi marmem can make product lightweight, energy efficient.
(4) description of drawings
Fig. 1 is an overall structure schematic representation of the present invention;
Fig. 2 is the turbofan engine structural representation that has NiTi marmem blade interior ventilation heating equipment;
Fig. 3 is the turbofan engine structural representation that has NiTi marmem blade exterior ventilation heating equipment;
Fig. 4 is the NiTi marmem blade shape A schematic representation that big bypass ratio is provided;
Fig. 5 is the NiTi marmem blade shape B schematic representation that little bypass ratio is provided;
Fig. 6 is a kind of internal structure schematic representation of hollow NiTi marmem blade;
Fig. 7 is hollow NiTi marmem blades flows schematic representation for hot air gets into;
Fig. 8 is ventilation heating equipment internal structure schematic representation.
(5) embodiment
For example the present invention is described further below in conjunction with accompanying drawing.
Embodiment 1: combine Fig. 1, Fig. 2, Fig. 3; A kind of deformable turbofan engine NiTi marmem blade of the present invention; It is made up of NiTi marmem blade (1), by-pass air duct (2), ventilation heating equipment (3), switch (4), main duct (5) and ventilation heating equipment internal structure (7); NiTi marmem blade (1) is positioned at the turbofan engine internal structure foremost, and ventilation heating equipment (3) left end is positioned at NiTi marmem blade (1) to be located, and right-hand member is positioned at motor main duct (5) and locates; Switch (4) is positioned at the left end of ventilation heating equipment (3); Ventilation heating equipment internal structure (7) is positioned at the right-hand member of ventilation heating equipment (3), and the right of NiTi marmem blade (1) is by-pass air duct (2) and main duct (5), and by-pass air duct (2) is positioned at the outside of main duct (5).The present invention also has following technical characteristics: described NiTi marmem blade has shape A and shape B;, adopts by motor shape A when needing big bypass ratio; When little bypass ratio, adopt shape B, at state 1 corresponding blade profile A, at state 2 corresponding blade profile B.Described ventilation heating equipment (3) is controlled its working state by switch (4) and turbine (9), opens switch (4) when NiTi marmem leaf temperature need raise and keep, and turbine (9) work just can feed hot air.
Embodiment 2: combine Fig. 4, Fig. 5; Aircraft is when taking off with subsonic velocity flight; Motor needs big bypass ratio, and airplane engine NiTi marmem leaf temperature is more constant, with critical temperature T1 (the temperature M that T1 corresponding martensitic phase transformation finish of temperature at this moment as state 1
f).When being lower than temperature T 1, use be the blade profile A (like Fig. 4) that big bypass ratio can be provided, what this profile adopted is compound design of plunderring type; Motor is climbing, is needing smaller duct recently improve engine operation efficient when acceleration and supersonic flight; (T2＞T1, T2 are the phase transition temperature A that martensitic phase converts parent phase fully into to make NiTi marmem leaf temperature rise to T2 through heating equipment
f) and holding temperature more than T2, at this moment marmem undergoes phase transition, and is referred to as state 2, NiTi marmem blade becomes profile B as shown in Figure 5, and less bypass ratio can be provided.NiTi marmem blade changes to profile B as shown in Figure 5 by profile A shown in Figure 4, and temperature rises to T2 by T1, keeps temperature more than or equal to T2, and blade is kept profile B; As will get back to big bypass ratio state once more and only need control heating equipment, cooling to smaller or equal to T1, NiTi marmem blade becomes profile A by profile B.
Embodiment 3: for the heating control mode of NiTi marmem blade, can adopt the mode of electric heating blade, this control mode ratio is easier to realize.Be warming up to state 2 like need, energising is heated to temperature T
2, continue the energising holding temperature more than or equal to T
2Just can keep blade profile B.
Embodiment 4: combine Fig. 2,, Fig. 7, Fig. 8, before the firing chamber, air is through the compression of press machine, temperature is greatly improved, and the air is here fed hollow blade inner (like Fig. 7) through heating equipment, thereby play the effect of heating.NiTi marmem blade is by temperature T
1Rise to T
2Process; Open heating equipment switch (4); Turbine among Fig. 8 (9) begins to rotate, and hot air just can pass through ventilation heating equipment (3) and get into hollow NiTi marmem blade (6) inside, and is as shown in Figure 7; Hot-fluid gets into NiTi marmem blade interior and after circulating, flows out at little opening, reaches temperature T
2Back maintained switch is opened, and lasting ventilation keeps temperature more than or equal to T
2
Embodiment 5: combine Fig. 3, hot air also can be realized the effect that heats through the outside of ventilation heating equipment feeding NiTi marmem blade.Open switch (4) and pass through the outside that ventilation heating equipment (3) hot air is passed into NiTi marmem blade, reach temperature T
2The state that back maintained switch is opened, lasting ventilation can keep temperature.
Embodiment 6: aircraft is when taking off with subsonic velocity flight, and motor needs big bypass ratio, and airplane engine NiTi marmem leaf temperature is more constant, will be at this moment as state 1; Motor is climbing, is needing smaller duct recently improve engine operation efficient when acceleration and supersonic flight; Make NiTi marmem blade (1) temperature rise to T2 through heating equipment (3); And holding temperature is more than T2; At this moment marmem undergoes phase transition, and is referred to as state 2.The temperature M that the corresponding martensitic phase transformation of critical temperature T1 finishes
fCritical temperature T2 is the phase transition temperature A that martensitic phase converts parent phase fully into
fThe phase transition temperature of NiTi marmem and the content of Ni are had very big relation, for example when Ni content is 49.1%, when the content of Ti is 50.9%, M
fBe about 40 ℃, A
fBe about 116 ℃.At this moment can get critical temperature T1 and be 40 ℃, critical temperature T2 is 116 ℃.
Claims (3)
1. deformable turbofan engine NiTi marmem blade; It is made up of NiTi marmem blade (1), by-pass air duct (2), ventilation heating equipment (3), switch (4), main duct (5) and ventilation heating equipment internal structure (7); It is characterized in that: NiTi marmem blade (1) is positioned at the turbofan engine internal structure foremost; Ventilation heating equipment (3) left end is positioned at NiTi marmem blade (1) and locates; Right-hand member is positioned at motor main duct (5) to be located, and switch (4) is positioned at the left end of ventilation heating equipment (3), and ventilation heating equipment internal structure (7) is positioned at the right-hand member of ventilation heating equipment (3); The right of NiTi marmem blade (1) is by-pass air duct (2) and main duct (5), and by-pass air duct (2) is positioned at the outside of main duct (5).
2. a kind of deformable turbofan engine NiTi marmem blade according to claim 1; It is characterized in that: described NiTi marmem blade (1) has shape A and shape B;, adopts by motor shape A when needing big bypass ratio; When little bypass ratio, adopt shape B, at state 1 corresponding blade profile A, at state 2 corresponding blade profile B.
3. a kind of deformable turbofan engine NiTi marmem blade according to claim 1; It is characterized in that: described ventilation heating equipment (3) is controlled its working state by switch (4) and turbine (9); When need raising and keep, NiTi marmem leaf temperature opens switch (4); Turbine (9) work just can feed hot air.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011103751969A CN102400718A (en) | 2011-11-23 | 2011-11-23 | NiTi shape memory alloy blade for deformable turbofan engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011103751969A CN102400718A (en) | 2011-11-23 | 2011-11-23 | NiTi shape memory alloy blade for deformable turbofan engine |
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| CN102400718A true CN102400718A (en) | 2012-04-04 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3321472A1 (en) * | 2016-11-14 | 2018-05-16 | United Technologies Corporation | A fan blade for a gas turbine engine and corresponding gas turbine engine |
| CN108076601A (en) * | 2016-11-15 | 2018-05-25 | 波音公司 | For the method for activating panel and equipment and aircraft including the panel |
| US11441545B2 (en) * | 2020-02-25 | 2022-09-13 | General Electric Company | Tungsten-based erosion-resistant leading edge protection cap for rotor blades |
| US11486349B2 (en) | 2020-01-10 | 2022-11-01 | General Electric Company | Methods for manufacturing blade structures |
| US11668317B2 (en) | 2021-07-09 | 2023-06-06 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
| US11674399B2 (en) | 2021-07-07 | 2023-06-13 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
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| CN101169047A (en) * | 2006-10-26 | 2008-04-30 | 通用电气公司 | Rotor blade profile optimization |
| US20100236244A1 (en) * | 2006-06-28 | 2010-09-23 | Longardner Robert L | Heat absorbing and reflecting shield for air breathing heat engine |
| US20110189014A1 (en) * | 2008-07-18 | 2011-08-04 | Mtu Aero Engines Gmbh | Gas turbine and method for varying the aerodynamic shape of a gas turbine blade |
| US8033789B2 (en) * | 2006-05-17 | 2011-10-11 | Rolls-Royce Plc | Apparatus for preventing ice accretion |
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Patent Citations (5)
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| US20060018761A1 (en) * | 2004-07-02 | 2006-01-26 | Webster John R | Adaptable fluid flow device |
| US8033789B2 (en) * | 2006-05-17 | 2011-10-11 | Rolls-Royce Plc | Apparatus for preventing ice accretion |
| US20100236244A1 (en) * | 2006-06-28 | 2010-09-23 | Longardner Robert L | Heat absorbing and reflecting shield for air breathing heat engine |
| CN101169047A (en) * | 2006-10-26 | 2008-04-30 | 通用电气公司 | Rotor blade profile optimization |
| US20110189014A1 (en) * | 2008-07-18 | 2011-08-04 | Mtu Aero Engines Gmbh | Gas turbine and method for varying the aerodynamic shape of a gas turbine blade |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3321472A1 (en) * | 2016-11-14 | 2018-05-16 | United Technologies Corporation | A fan blade for a gas turbine engine and corresponding gas turbine engine |
| US10428825B2 (en) | 2016-11-14 | 2019-10-01 | United Technologies Corporation | Airfoil structure having a shape memory alloy actuator |
| CN108076601A (en) * | 2016-11-15 | 2018-05-25 | 波音公司 | For the method for activating panel and equipment and aircraft including the panel |
| US11486349B2 (en) | 2020-01-10 | 2022-11-01 | General Electric Company | Methods for manufacturing blade structures |
| US11441545B2 (en) * | 2020-02-25 | 2022-09-13 | General Electric Company | Tungsten-based erosion-resistant leading edge protection cap for rotor blades |
| US11674399B2 (en) | 2021-07-07 | 2023-06-13 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
| US11668317B2 (en) | 2021-07-09 | 2023-06-06 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
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Application publication date: 20120404 |