阅读说明：本技术 冲压空气涡轮 (Ram air turbine ) 是由 洪烨 周绚 杨溢炜 浦程楠 赵文豪 王帮亭 于 2021-11-02 设计创作，主要内容包括：本发明涉及一种用于飞机的冲压空气涡轮叶片组件,包括：形成容纳腔的框架；叶片,叶片的连接部从敞开的端部接纳到容纳腔内,在发电功率要求较大情况下,能够从初始位置移动到延伸位置之间移动,在初始位置,叶片的接部相对框架的容纳腔缩进,在延伸位置,叶片的连接部的一部分相对框架的容纳腔伸出；卡锁装置,卡锁装置构造成当叶片的连接部在延伸位置时将叶片的连接部相对框架锁止；以及阻尼装置,阻尼装置构造成向所述叶片施加与离心力方向相反的阻尼力。采用根据本发明的叶片组件,能够增加空气冲压涡轮的发电功率增大,能够有效应对大功率负载的工况,并且,对于舱门的尺寸要求较小,冲压空气涡轮在飞机中安装位置的可适性随之增加。(The invention relates to a ram air turbine blade assembly for an aircraft, comprising: a frame forming a receiving cavity; the connecting part of the blade is received into the accommodating cavity from the open end part and can move between an initial position and an extended position under the condition of large power generation requirement, the connecting part of the blade retracts relative to the accommodating cavity of the frame at the initial position, and a part of the connecting part of the blade extends relative to the accommodating cavity of the frame at the extended position; a latch configured to lock the connecting portion of the blade relative to the frame when the connecting portion of the blade is in the extended position; and a damping device configured to apply a damping force to the blade in a direction opposite to a centrifugal force. By adopting the blade assembly provided by the invention, the generated power of the air ram turbine can be increased, the working condition of a high-power load can be effectively coped with, the size requirement on the cabin door is smaller, and the adaptability of the installation position of the ram air turbine in an airplane is increased.)

1. A blade assembly for an aircraft ram air turbine, comprising:

a frame in which a receiving cavity is formed, one end of the receiving cavity being open;

a blade having a connecting portion received into the receiving cavity from an open end and movable between an initial position in which the connecting portion of the blade is retracted relative to the receiving cavity of the frame and an extended position in which a portion of the connecting portion of the blade is extended relative to the receiving cavity of the frame;

a latch device configured to lock the connecting portion of the blade relative to the frame when the connecting portion of the blade is in the extended position; and

a damping device configured to apply a damping force to the blade opposite to a direction of a centrifugal force.

2. The blade assembly according to claim 1, characterized in that said frame has a pair of tracks formed on opposite sides of said receiving cavity,

the blade assembly further includes a pair of moving slot devices secured to both sides of the connecting portion of the blade, each of the pair of moving slot devices slidably engaging a corresponding one of the pair of rails.

3. The blade assembly according to claim 2, characterized in that said blade assembly further comprises a slip lock configured to lock said blade relative to the frame when said connection portion of said blade is in said initial position.

4. The blade assembly according to claim 3, characterized in that the glide lock is included in the moving slot arrangement, the glide lock being configured to lock the moving slot arrangement relative to the rail such that the blade is locked relative to the frame at the initial position.

5. The blade assembly according to claim 3 or 4, characterized in that said slip lock is connected to an electromagnetic control mechanism which unlocks said slip lock when the centrifugal force reaches a preset threshold.

6. The blade assembly according to claim 1, characterized in that said damping means comprise a spring arranged at the end of said housing cavity of said frame opposite to said open end, one end of said spring being fixed to said blade and the other end of said spring being fixed to said connection portion of said blade.

7. The blade assembly according to claim 1, characterized in that said latch means has a locking pin and a resilient member arranged to act on said locking pin to exert a resilient force on said locking lock, said connecting portion of said blade being provided with a locking hole through which said locking pin engages said blade when said blade reaches said extended position.

8. The blade assembly according to claim 7, characterized in that said latch means are arranged in an upper or lower wall of said housing cavity of said frame, and in a position intermediate in the transverse direction of said connection portion of said blade.

9. The blade assembly according to claim 7, characterized in that said connecting portion of said blade is provided with a first and a second clipping hole, said extended positions comprising a first extended position and a second extended position,

wherein the first detent hole is positioned such that the connecting portion of the blade is in the first extended position when the locking pin passes through the first detent hole,

wherein the second detent hole is positioned such that the connecting portion of the blade is in the second extended position when the locking pin passes through the second detent hole.

10. The blade assembly according to claim 8, characterized in that a spacer is provided on the surface of said connecting portion of said blade facing said latch means.

Technical Field

The present invention relates to ram air turbines for aircraft, and more particularly to a ram air turbine with extendable blades.

Background

Ram Air Turbines (RATs) are designed for emergency forced landing of aircraft when primary and secondary power is lost to improve survivability of the aircraft. The system works by utilizing the kinetic energy of the airplane, under a specific condition, a propeller of a ram air turbine is put down from a non-airtight cabin of the airplane in an emergency mode, the propeller is impacted by rapid air incoming flow, and the high-speed rotary motion of the propeller drives a motor and a hydraulic pump connected with the propeller to generate necessary emergency energy for restarting an engine and ensuring the emergency function power supply of an airplane operating system, a hydraulic system and electronic equipment.

In the emergency power mode of the C919 aircraft, the problem of ram air turbine system loading has always been one of the most important issues, including the start of the ac electric pump (ACMP), the on-board critical bus bars and related equipment all placing demands on the power generation system.

For ram air turbines that benefit from aerodynamic forces to generate energy, it is desirable for the blades to be as efficient as possible for wind energy use in order to address the loading problem. According to the traditional wind power generation system, the wind energy utilization coefficient is related to relevant angles and other factors, under the condition that the wind energy utilization efficiency is certain, the larger the blade radius is, the stronger the power generation power is, however, the problem of interference between the blade and the cabin door is caused by the increase of the blade diameter, the structural weight and the cost of the cabin door caused by the large-diameter blade are increased, and meanwhile, the adaptability of the installation position of the ram air turbine is reduced. Accordingly, there is a need to be able to retrofit existing blade assemblies of ram air turbines to meet the dual requirements related to ram air turbine system release operation and to wind energy utilization efficiency.

Disclosure of Invention

To overcome the deficiencies in the prior art, the present invention provides a blade assembly for an aircraft ram air turbine, comprising: a frame in which a receiving cavity is formed, one end of the receiving cavity being open; a blade having a connecting portion received into the receiving cavity from an open end and movable between an initial position in which the connecting portion of the blade is retracted relative to the receiving cavity of the frame and an extended position in which a portion of the connecting portion of the blade is extended relative to the receiving cavity of the frame; a latch device configured to lock the connecting portion of the blade relative to the frame when the connecting portion of the blade is in the extended position; and a damping device configured to apply a damping force to the blade opposite to a direction of a centrifugal force.

According to another aspect of the invention, the frame has a pair of rails formed on opposite sides of the receiving cavity, and the blade assembly further includes a pair of moving slot devices secured to opposite sides of the connecting portion of the blade, each of the pair of moving slot devices slidably engaging a corresponding one of the pair of rails.

According to yet another aspect of the present invention, the blade assembly further comprises a slip lock configured to lock the blade with respect to the frame when the connection portion of the blade is in the initial position.

According to a further aspect of the invention, the sliding lock is comprised in the moving card-slot arrangement, the sliding lock being configured to lock the moving card-slot arrangement relative to the rail such that the blade is locked relative to the frame at the initial position.

According to a further aspect of the invention, said slip lock is connected to an electromagnetic control mechanism which unlocks said slip lock when the centrifugal force reaches a preset threshold.

According to a further aspect of the present invention, the damping means includes a spring disposed at an end of the receiving chamber of the frame opposite to the open end, one end of the spring being fixed to the housing, and the other end of the spring being fixed to the connecting portion of the blade.

According to a further aspect of the present invention, the latch device has a locking pin and an elastic member arranged to act on the locking pin to apply an elastic force to the locking lock, the connecting portion of the vane is provided with a catching hole through which the locking pin catches the vane when the vane reaches the extended position.

According to still another aspect of the present invention, the latch means is disposed in an upper wall or a lower wall of the receiving cavity of the frame at a position intermediate in a lateral direction of the connecting portion of the blade.

According to a further aspect of the present invention, the connecting portion of the blade is provided with a first engaging hole and a second engaging hole, and the extended positions include a first extended position and a second extended position, wherein the first engaging hole is positioned such that the connecting portion of the blade is in the first extended position when the lock pin passes through the first engaging hole, and wherein the second engaging hole is positioned such that the connecting portion of the blade is in the second extended position when the lock pin passes through the second engaging hole.

When the blade is simultaneously provided with the first clamping hole and the second clamping hole, the same ram air turbine with the blade assembly can adapt to airplanes of different scales, and when the requirement on the power of the airplane to the ram air turbine is not high, the locking pin can penetrate through the second clamping hole by setting the initial position of the clamping head, namely, the second clamping hole 33 in fig. 1 is penetrated by the locking pin, so that the blade is always kept at the first position in the use process of the ram air turbine.

According to a further aspect of the invention, a spacer is provided on the surface of the connecting portion of the blade facing the latch means.

The spacer is arranged between the connecting part and the clamping and locking bone device, so that the blade can be protected, and the clamping head of the clamping and locking device is prevented from damaging the surface of the blade in the process of outward sliding of the blade.

By adopting the blade assembly provided by the invention, when the ram air turbine is completely released, the blades can extend outwards, so that the outer diameter of the whole impeller is increased, the radius of the blades is increased under the condition of certain wind energy utilization efficiency, the power generation power is increased, and the working condition of a high-power load can be effectively coped with.

With the blade assembly according to the invention, the radius of the ram air turbine is at a minimum when it is released through the cabin door, so that the dimensional requirements for the cabin door are smaller and the adaptability of the installation location of the ram air turbine in the aircraft is increased. Furthermore, the blade assembly of the ram air turbine is telescopic, which also reduces the structural and weight requirements of the ram air turbine door, reducing the corresponding structural costs.

Drawings

For a more complete understanding of the present invention, reference is made to the following description of exemplary embodiments taken in conjunction with the accompanying drawings, in which:

FIG. 1 illustrates a perspective view of a blade assembly of a ram air turbine in accordance with a preferred embodiment of the present invention.

FIG. 2 illustrates a perspective view of a latch arrangement for a blade assembly of a ram air turbine according to a preferred embodiment of the present invention.

FIG. 3 illustrates a schematic perspective view of a blade assembly in an initial position according to a preferred embodiment of the present invention.

FIG. 4 illustrates a schematic perspective view of a blade assembly in an extended position according to a preferred embodiment of the present invention.

FIG. 5 illustrates an end view of a blade assembly according to a preferred embodiment of the present invention.

FIG. 6 illustrates a schematic exterior view of a turbine blade according to a preferred embodiment of the present invention.

List of reference numerals

10 blade assembly

20 frame

21 accommodating cavity

221 open end

22 track strip

30 blade

31 connecting part

32 card hole

33 auxiliary clip hole

40 mobile card slot device

41 sliding locking piece

50 locking device

51 locking pin

53 spring

55 liner bushing

60 damping device

70 turbine disk

Detailed Description

The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.

In the following description, the upper and lower parts are described based on the illustrated positions, and are only for clear indication, and the positions are not limited by nature.

FIG. 1 illustrates a perspective view of one blade assembly 10 of a ram air turbine in accordance with a preferred embodiment of the present invention. The blade assembly 10 generally includes a frame 20 and a blade 30 mounted to the frame 20. The frame 20 is typically integrated into a turbine disk 70 as shown in fig. 5. in ram air turbine operation, the blades 30 are rotated by the wind, causing the frame 20 to rotate therewith, thereby causing the turbine disk 70 to rotate, and thereby causing the autonomous power generation system to operate to deliver power.

As shown in fig. 1, the blade assembly 10 frame 20 has a receiving cavity 21 formed therein, the receiving cavity 21 having a substantially flat rectangular parallelepiped shape, and one end of the receiving cavity 21 being open for receiving the connecting portion 31 of the blade 30. Preferably, a bushing 55 (see fig. 1) may be provided at the open end of the receiving cavity 21 to prevent water from entering the protruding port of the blade 30 and lightning.

The connecting portion 31 of the vane 30 shown in fig. 1 has a shape corresponding to the receiving cavity 21. The blade 30 also includes a blade portion that directly receives wind action and is omitted for simplicity. Preferably, the blade portion and the connecting portion 31 of the blade 30 are integrally formed. It should be understood that in alternative embodiments, the blade may be formed from several segments that are assembled together.

As shown in fig. 3 and 4, in the accommodation chamber 21, the connection portion 31 of the vane 30 is movable from an initial position shown in fig. 3 to an extended position shown in fig. 4. When the connecting portion 31 of the vane 30 is located at the initial position, the connecting portion 31 of the vane 30 is retracted with respect to the receiving cavity 21 of the frame 20, and when the connecting portion 31 of the vane 30 is located at the extended position, the connecting portion 31 of the vane 30 is protruded from the receiving cavity 21 of the frame 20. Thus, when the connecting portion 31 of the vane 30 is in the initial position, the entire vane 30 is in the retracted position, and thus, the entire impeller has the smallest diameter. When the connecting portion 31 of the vane 30 is in the extended position, the entire vane 30 is in its extended state, so that the entire impeller has a maximum extended diameter.

To enable sliding of the blade 30 with respect to the frame 20, the frame 20 has pairs of rails on opposite sides of the housing 21. A movable card slot device 40 is arranged on each track in a sliding way, the card slot device 40 slides along with the sliding of the blade 30, and the sliding range of the card slot device 40 is the track range. The attachment portion 31 of the blade 30 is secured to the moving-slot arrangement 40 by a fastener or fastening structure so that sliding movement of the blade 30 relative to the frame 20 is achieved by sliding movement of the moving-slot arrangement 40 relative to the track.

In the preferred embodiment, as shown in figure 5, the tracks on each side are formed by a strip of track 22 of T-section projecting over the side wall of the housing 21. The mobile-card-slot arrangement 40 includes a corresponding T-shaped recess, and engagement between the T-shaped recess and the T-section rail 22 causes the mobile-card-slot arrangement 40 to engage the rail 22 on both the upper and lower surfaces of the rail 22, respectively. On the other hand, as can also be seen from fig. 5, in the moving-card-slot device 40, on the side opposite to the T-shaped recess, there is also provided a recess that engages the connecting portion 31 of the blade 30.

It should be understood that the manner of forming the track is not limited to the above-described embodiment, and in alternate embodiments, the track in the moving card-slot arrangement and the receiving cavity may have other complementary shapes or configurations, so long as the sliding movement between the two is achieved under the influence of centrifugal force.

As shown in fig. 1, a slide lock 41 is also provided in the mobile slot device 40, and is configured to lock the mobile slot device 40 relative to the rail, in which case the mobile slot device 40 cannot move relative to the rail strip 22 in the receiving cavity 21. Specifically, when the connecting portion 31 of the paddle 30 is in the retracted initial position, the slide lock 41 of the moving pocket device 40 is in the locked state.

Preferably, the slip lock 41 comprises an electromagnetically actuated slip lock 41, and the slip lock 41 may engage a recess or recess provided in the wall of the track bar 22 or frame 20 to effect locking. The electromagnetic control signal of the sliding lock 41 is related to the centrifugal force or the rotating speed, during the release process of the ram air turbine, the blade 30 starts to rotate, the rotating speed is increased, the generated centrifugal force is increased, the centrifugal force exceeds a set threshold value, the control device provides an unlocking signal to the electromagnetic sliding lock 41, so that the sliding lock 41 is unlocked, and the movable slot device 40 can slide relative to the track.

In the preferred embodiment, each of the moving card-slot arrangements 40 on either side of the receiving cavity 21 has various slide locks 41, and the two moving card-slot arrangements 40 are symmetrically arranged with respect to the connecting portion 31 of the blade 30.

It should be understood that in other alternative embodiments, the slide lock 41 may be provided separately from the mobile slot device 40. For example, the slide lock is not provided in the moving-card-slot device 40, but is provided separately on one of the connecting portion 31 of the blade 30 and the wall of the housing chamber 20, and is capable of engaging a complementary lock provided on the other of the connecting portion 31 of the blade 30 and the wall of the housing chamber 20.

Further, in the blade assembly 10 according to the preferred embodiment of the present invention, a damping device 60 configured to apply a damping force to the blade 30 in a direction opposite to a centrifugal force generated when the turbine rotates is provided between the frame 20 and the blade 30. Thus, the damping device 60 is used to apply a damping force to the blade 30 during the outward sliding of the blade 30, so as to slow down the blade 30 and avoid the sliding speed of the blade 30 from being too fast.

In the preferred embodiment, the damping device 60 is a spring, one end of which is fixed to the frame 20 and the other end of which is fixed to the connecting portion 31 of the blade 30, and as shown in fig. 4, when the blade 30 moves outward, the spring is stretched and the stretched spring applies a restoring elasticity to the blade 30 to resist a part of the centrifugal force.

It should be understood that other alternative configurations and alternative locations for the damping device are possible, and that the damping device 60 may not be located at the end of the frame 20 distal from the open end, for example, the damping device may be located at the track of the frame 20 to apply a damping force against the centrifugal force to the moving pocket device 40 to slow the outward extension of the blades 30.

Further, the blade assembly 10 according to the preferred embodiment of the present invention further comprises a latch device 50 configured to lock said connecting portion 31 of said blade 30 in said extended position with respect to the frame 20. As shown in fig. 1, the latch device 50 is provided at an upper wall or a lower wall of the frame 20, and is located at a substantially middle position in a lateral direction of the connecting portion 31 of the blade 30. As shown in fig. 2, the latch device 50 has a locking pin 51 and an elastic member 53, and the coupling portion 31 of the vane 30 is provided with a locking hole 32, and an opposite wall of the frame 20 is also provided with a hole or a recess aligned with the locking pin 51. When the attachment portion 31 of the blade 30 reaches the extended position, the locking pin 51 passes through the locking hole 32 of the blade 30 and is inserted into a hole or recess in the frame 20, so that the blade 30 is locked and cannot slide any further outward. In the preferred embodiment, the top of the locking pin 51 has a hemispherical head. As can be seen from fig. 1, in addition to the catching hole 32 away from the open end 221 of the accommodating chamber 21, an auxiliary catching hole 33 is provided on the connecting portion 31 of the blade 30 closer to the open end 221. The auxiliary latching hole 33 can be latched with the latching pin 51 of the latching device 50 in the extended position in which the connecting portion 31 of the blade 30 extends to a small distance from the receiving chamber 21. This arrangement is intended to meet the design requirements of ram air turbine small impellers. When the energy requirement of the aircraft on the ram air turbine is reduced, the same ram air turbine can be used, and the turbine of the small-diameter impeller can be obtained only by locking the locking device 50 with the auxiliary locking hole 33 so as to avoid the outward sliding of the blade 30 at any rotating speed.

It will be appreciated that when the latch means 50 is engaged with the latch aperture 33, with the position of the latch means 40 corresponding to the leftmost position of the track, the power requirement is lower and the blade 30 is held stationary at any rotational speed. It should be understood that if the power generation requirement is high and the blade 30 needs to be extended, the slot device 40 can move the blade 30 outward from the initial position shown in fig. 3, and when the locking hole 32 is locked by the locking pin 51, as shown in fig. 4, the position of the slot device 40 corresponds to the rightmost position of the rail, that is, the position corresponding to the blade 30 when extended and locked.

Furthermore, the ram air turbine according to the invention comprises a shim arranged between the blade 30 and the receiving chamber 21 of the frame 20, which shim prevents the clamping head of the locking pin 51 from wearing the surface of the blade 30 during the outward sliding of the blade 30.

In the ram air turbine, preferably, the frame 20 is integrally embedded in the turbine disk 70, the housing cavities 21 being symmetrically arranged in the frame 20 and correspondingly symmetrically receiving the blades 30. The symmetrical arrangement of the blades 30 allows the same centrifugal force to be experienced on each blade 30 during ram air turbine release.

The following description is provided in the context of use of a ram air turbine having a blade assembly 10 according to a preferred embodiment of the present invention.

When the aircraft encounters a particular situation, the hatch of the ram air turbine is opened and the ram air turbine is released from the interior of the fuselage outwards, at which point the connection 31 of the blade 30 is in a retracted initial position with respect to the housing 21 of the frame 20, the diameter of the impeller made up of a plurality of blades 30 being minimized. As the ram air turbine blade assembly 10 is released and positioned in the air, the air flow rotates the blades 30, and when the rotational speed or the centrifugal force generated by the rotation reaches a predetermined threshold, the control device controls the locking pin in the moving-slot device 40 to be unlocked, and the moving-slot device 40 moves radially outward along the track under the centrifugal force generated by the rotation of the blades 30, and the blades 30 further extend outward, so that the diameter of the impeller becomes larger. During the outward movement of the blade 30, the damping force applied by the spring damping device 60 to the blade 30 is also gradually increased, so as to reduce or maintain the outward movement speed of the blade 30 against the gradually increasing centrifugal force. When the connecting portion 31 of the blade 30 reaches the extended position, the locking member of the locking device is aligned with the locking hole 32 on the connecting portion 31 of the blade 30 with the aid of the damping device 60, the locking member is pushed into the locking hole of the connecting portion 31 by the elastic member of the locking device, and then engages into the recess or hole in the wall of the frame 20, the blade 30 can no longer move outward, and the impeller reaches the maximum outer diameter. In this way, the ram air turbine can be operated with an increased impeller radius.

With the blade assembly 10 according to the present invention, when the ram air turbine is fully released, the blades 30 can extend outward, so that the outer diameter of the entire impeller is increased, in a preferred embodiment, the outer diameter can be increased by 8-10 cm, and under the condition of a certain wind energy utilization efficiency, the radius of the blades 30 is increased, so that the generated power is increased, and the working condition of a high power load can be effectively coped with.

With the blade assembly 10 according to the invention, the radius of the ram air turbine is at a minimum when it is released through the cabin door, so that the dimensional requirements for the cabin door are smaller and the adaptability of the installation location of the ram air turbine in the aircraft is increased. Furthermore, the blade assembly 10 of the ram air turbine is telescopic, which also reduces the structural and weight requirements of the ram air turbine door, reducing the corresponding structural costs.

Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.