Ram air turbine emergency power unit and aircraft

Abstract

The present application relates to a ram air turbine emergency power drive device, comprising: a first set of turbine blades and a second set of turbine blades coaxially arranged in an axial direction, wherein the second set of turbine blades can be rotated relative to the first set of turbine blades around the axial direction from a first position to a second position and kept in the second position, wherein in the first position, the first set of turbine blades is superposed with the second set of turbine blades, and in the second position, the first set of turbine blades is at a predetermined non-zero angle with the second set of turbine blades. In this way, the number of blades is increased without affecting the space in the ram air turbine cabin, so that the turbine starting speed is faster, and the RAT access to the power grid time is reduced. In addition, increasing the number of blades can also improve the efficiency of the turbine in converting wind energy, thereby improving the efficiency of the emergency power generation. The present application also relates to an aircraft comprising the ram air turbine emergency power drive device.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft emergency power drive systems, and relates to a ram air turbine emergency power drive device, and more particularly to a rotatable and expandable aircraft emergency power turbine drive structure. In addition, the present application also relates to an aircraft. BACKGROUND

[0002] The ram air turbine (RAT) emergency power generation device is an emergency turbine generator set used by the aircraft when the dual generator fails. It is driven by the aerodynamic force generated by the flow field of the aircraft in flight, and provides the hydraulic power required for emergency landing operation and the power required by the electrical user.

[0003] The ram air turbine emergency power generation device works by utilizing the aerodynamic energy of the aircraft. In an emergency condition, the ram air turbine is released from the aircraft, and the ram air turbine drives the turbine blades using the rapid ram air flow. The turbine is connected to the generator or hydraulic drive pump through a gearbox.

[0004] The ram air turbine emergency power drive device of large civil aircraft is usually arranged in a good aerodynamic performance area. The specific arrangement position needs to balance various factors such as blade size and arrangement space, and finally the optimal scheme is obtained. Due to the space limitation on the aircraft, the current design of the ram air turbine is usually a double-blade structure. In order to improve the power generation efficiency, the length or number of blades needs to be increased. However, the larger cabin door opening will affect the strength of the main structure of the aircraft. Therefore, due to the size limitation of the RAT cabin door opening, the number of RAT blades is generally limited to a two-blade structure.

[0005] In order to improve the power generation efficiency and reduce the occupied volume and maintenance cost of the ram air turbine, an invention patent with the title of "A ram air turbine variable pitch mechanism" and the publication number of CN108775262A was filed by Beijing Petroleum Chemical College on May 30, 2018, which proposes a ram air turbine variable pitch mechanism arranged in the shell of the ram air turbine and connected with the blades through a blade connecting shaft, including a front part and a rear part of the gear strip frame plate fixed transversely in the shell and an expansion joint secondary baffle, an expansion joint baffle is arranged between the gear strip frame plate and the expansion joint secondary baffle, a gear strip is installed between the gear strip frame plate and the expansion joint baffle, and an expansion joint is arranged between the expansion joint baffle and the expansion joint secondary baffle; the gear strip is engaged with the gear fixed in the inner end of the blade connecting shaft. The ram air turbine blade can always maintain the best angle of attack during work, and can automatically become feathered after work. However, this structure is still a two-blade structure, and the improvement of power generation efficiency is limited.

[0006] Therefore, it is urgent to optimize the structure of the ram air turbine emergency power driving device, which can overcome one or more shortcomings in the prior art. SUMMARY

[0007] The object of the present application is to provide a ram air turbine emergency power driving device which, by increasing the number of blades, makes the turbine start-up speed faster, can reduce the RAT access to the power grid time, greatly improves the efficiency of the turbine in converting energy from wind power and the emergency power generation efficiency, and can improve the heavy load carrying capacity and reduce the low-speed power supply limit envelope.

[0008] According to one aspect of the present application, a ram air turbine emergency power driving device is proposed, which can include:

[0009] a first set of turbine blades and a second set of turbine blades arranged coaxially in an axial direction, wherein the second set of turbine blades can be rotated about the axial direction from a first position to a second position relative to the first set of turbine blades and held in the second position,

[0010] wherein in the first position, the first set of turbine blades is superimposed with the second set of turbine blades, and in the second position, the first set of turbine blades is at a predetermined non-zero angle with the second set of turbine blades.

[0011] In this way, under the condition of ensuring not to affect the space inside the ram air turbine cabin, the number of blades is increased, so that the turbine start-up speed is faster, and the RAT access to the power grid time is reduced. In addition, increasing the number of blades can also improve the efficiency of the turbine in converting energy from wind power, thereby improving the emergency power generation efficiency.

[0012] According to the above aspect of the present application, preferably, the first set of turbine blades can be fixed to a first mounting member, and the second set of turbine blades can be fixed to a second mounting member, wherein the first mounting member and the second mounting member have a complementary shape fitting structure, so that in the second position, the first mounting member and the second mounting member are fitted together and limit the movement of the second mounting member relative to the first mounting member.

[0013] In this way, by fitting the first mounting member and the second mounting member together through shape fitting, and then making the first set of turbine blades relative to the second set of turbine blades remain fixed in the second position, the stable and safe operation of the ram air turbine emergency power driving device is ensured.

[0014] According to the above aspect of the present application, preferably, the first mounting member can comprise a first shaft provided with a radial protrusion at an end facing the second mounting member, and the second mounting member can comprise a receiving portion configured to guide the radial protrusion in an axial direction, and wherein the receiving portion is provided with a reduced diameter portion at an end facing the first mounting member.

[0015] With such an axial arrangement, the first set of turbine blades and the second set of turbine blades can not only be rotated relative to each other in a circumferential direction, but also be moved relative to each other in an axial direction to adjust the axial distance between the first set of turbine blades and the second set of turbine blades, thereby further improving the efficiency of converting wind energy into power.

[0016] According to the above aspect of the present application, preferably, the first mounting member can comprise a first flange and a first groove spaced apart around a circumferential direction, and the second mounting member can comprise a second flange and a second groove spaced apart around the circumferential direction, wherein in the second position, the first flange fits into the second groove, and the second flange fits into the first groove.

[0017] With such an arrangement, it can be ensured that in the second position, the first mounting member and the second mounting member are more reliably fixed together by means of a form fit, ensuring the reliability and stability of the coupling, in particular in the circumferential direction and the axial direction.

[0018] According to the above aspect of the present application, preferably, the first flange can be provided with a first sliding rail, and the first groove can be provided with a second sliding rail, and the second flange is provided with a first sliding block, wherein in the first position, the first sliding block fits into the first sliding rail, and in the second position, the first sliding block fits into the second sliding rail.

[0019] In this way, the first mounting member and the second mounting member can be moved relative to each other according to a predetermined path, in particular a circumferential movement, and ensure the reliability and stability of the coupling, in particular in the radial direction.

[0020] According to the above aspect of the present application, preferably, the first sliding rail can form a through opening towards an end of the first flange in a first circumferential direction, and be closed at an opposite end to constrain the second mounting member to rotate relative to the first mounting member only in the first circumferential direction.

[0021] In this way, the first sliding rail is only open in one direction to allow the second mounting member to only be able to rotate relative to the first mounting member in one direction, and only be able to rotate through a circumferential distance of one flange or groove, as the closed end prevents continued rotation of the second mounting member relative to the first mounting member, thereby avoiding idling of the second set of turbine blades relative to the first set of turbine blades as much as possible.

[0022] According to the above aspect of the present application, preferably, a biasing member can be provided between the first mounting member and the second mounting member, the biasing member biases the second mounting member towards the first mounting member. The biasing member can force the second mounting member to move closer to the first mounting member together with ram air.

[0023] According to the above aspect of the present application, alternatively and additionally preferably, a biasing member can be provided between the first mounting member and the second mounting member, the biasing member biases the second mounting member away from the first mounting member. The biasing member can help the second mounting member to return to the first position, i.e. the stowed position, relative to the first mounting member when there is no ram air acting on the second set of turbine blades, for example when the ram air turbine emergency power unit is not in operation (e.g. after the aircraft has landed), thereby facilitating the RAT stowing operation by maintenance personnel.

[0024] According to the above aspect of the present application, preferably, the first set of turbine blades and the second set of turbine blades can each comprise two turbine blades arranged in line. In this way, compared with the existing ram air turbine emergency power unit, the space requirement for installation and opening is not increased, facilitating the retrofit implementation on the existing aircraft.

[0025] According to the above aspect of the present application, preferably, in the second position, the first set of turbine blades and the second set of turbine blades can be in the same rotational plane, thereby further improving the wind energy utilization rate of the ram air turbine emergency power unit.

[0026] According to the above aspect of the present application, in order to further improve the wind energy utilization rate, preferably, in the second position, the first set of turbine blades and the second set of turbine blades can form an angle of 90 degrees.

[0027] According to another aspect of the present application, a kind of aircraft can be provided, which can include the ram air turbine emergency power unit according to any one of the above aspects.

[0028] The ram air turbine emergency power unit of the present application includes but is not limited to the following advantages listed:

[0029] 1) The device of the present application can greatly improve the efficiency of turbine energy conversion and emergency power generation by increasing the number of blades;

[0030] 2) The turbine of the device of the present application can start faster by increasing the number of blades, which can reduce the time of RAT access to the power grid;

[0031] 3) The device of the present application has stronger load carrying capacity, which can greatly improve the load carrying capacity of the turbine under heavy load;

[0032] 4) The device of the present application is more efficient in extracting wind energy and has less low-speed limit for emergency power supply by increasing the number of blades.

[0033] Thus, the ram air turbine emergency energy driving device of the present application can meet the use requirements, overcome the shortcomings of the prior art and achieve the predetermined purpose. BRIEF DESCRIPTION OF DRAWINGS

[0034] In order to further clearly describe the ram air turbine emergency energy driving device according to the present application, the present application will be described in detail below in combination with the drawings and specific embodiments, in which:

[0035] Figure 1 The wind energy utilization coefficient versus tip speed ratio relationship of the ram air turbine emergency energy driving device is schematically shown;

[0036] Figure 2 is a schematic view of the ram air turbine emergency energy driving device according to the non-limiting embodiment of the present application in a first position;

[0037] Figure 3 is a schematic view of the ram air turbine emergency energy driving device according to the non-limiting embodiment of the present application in a second position;

[0038] Figure 4 is a schematic perspective view of a part of the ram air turbine emergency energy driving device according to the present application;

[0039] Figure 5 is a schematic top view of a part of the ram air turbine emergency energy driving device according to the present application;

[0040] Figure 6 is a schematic perspective view of another part of the ram air turbine emergency energy driving device according to the present application; and

[0041] Figure 7 is a schematic sectional view of a part of the ram air turbine emergency energy driving device according to the present application.

[0042] The above-mentioned drawings are merely schematic and are not strictly drawn to scale.

[0043] The reference numerals in the drawings are listed in the list of drawings and embodiments:

[0044] 100 - ram air turbine emergency energy driving device, comprising:

[0045] 10 - first set of turbine blades;

[0046] 20 - second set of turbine blades;

[0047] 30 - first mounting member, comprising:

[0048] 30A - first shaft;

[0049] 31 - first flange;

[0050] 31 A - first slide rail;

[0051] 32 - first groove;

[0052] 32A - second slide rail;

[0053] 40 - second mounting member, comprising:

[0054] 40A - housing;

[0055] 41 - second flange;

[0056] 41 A - first slide block;

[0057] 42 - second groove;

[0058] 50 - biasing member;

[0059] A - axial direction;

[0060] B - first circumferential direction. DETAILED DESCRIPTION

[0061] It should be understood that the application can take, unless explicitly stated to the contrary, various alternative orientations and step sequences. It also should be understood that the specific devices illustrated in the attached drawings, and described in the following specification, are simply exemplary embodiments of the inventive concepts defined herein. Hence, specific dimensions, directions or other physical characteristics relating to the embodiments disclosed are not to be considered as limiting, unless expressly stated otherwise.

[0062] Ram air turbine (RAT) emergency power generator is an important equipment of emergency power system and hydraulic system of aircraft. RAT system is the last emergency means when the main engine of aircraft is stopped and auxiliary power unit (APU) is failed. RAT is normally stored inside the fuselage, inside the wing or in the hatch of landing gear. When working, ram air turbine is ejected, the front end blade is blown by the flow of airflow during flight and drives the engine or small hydraulic machine to work, providing emergency power supply or hydraulic supply for the aircraft.

[0063] Due to the space limitation on the aircraft, the current aircraft ram air turbine design is usually a double-blade structure. If the power generation efficiency is to be improved, the length or number of blades needs to be increased. Larger hatch opening will affect the strength of the main structure of the aircraft. Therefore, due to the size limitation of the RAT hatch opening, the number of RAT blades is generally limited to 2 blades.

[0064] Figure 1The relationship between the wind energy utilization coefficient and the tip speed ratio of the ram air turbine emergency power drive device is schematically shown.

[0065] The larger the blade size of the ram air turbine, the greater the tip speed ratio. The tip speed ratio is the ratio of the tip line speed of the wind wheel blade to the undisturbed airflow speed upstream of the turbine, denoted by λ, and the calculation formula is:

[0066]

[0067] where ω is the angular speed of the turbine rotation, with the unit of rad / s;

[0068] R is the radius of the turbine, with the unit of m;

[0069] v ∞ is the undisturbed airflow speed upstream of the turbine, with the unit of m / s.

[0070] Substitute ω = 2πn into the above formula, where n is the rotation speed of the turbine, with the unit of rpm / s, to obtain:

[0071]

[0072] The wind energy utilization coefficient refers to the ratio of the output power of the turbine to the wind power possessed by the free flow speed corresponding to the swept area of the turbine, denoted by C p , and thus the calculation formula of the output power P of the turbine is:

[0073]

[0074] where P is the output power of the turbine, with the unit of W;

[0075] ρ is the air density, with the unit of kg / m 3 ;

[0076] A d is the swept area of the turbine, with the unit of m 2 .

[0077] The rotation speed of the ram air turbine is generally 6800 rpm / min, the air speed of the aircraft in the air is greater than 130 kn (knots) and less than 0.8 ma (Mach), and if the radius of the ram air turbine is 0.6 m. If the blade shape and variable pitch are not considered, the tip speed ratio of the low-speed characteristics is estimated to be 5.57, at which time the wind energy utilization coefficient is 0.2 for 2 blades, and the wind energy utilization coefficient is 0.38 for 4 blades. The wind energy utilization rate and the turbine output power are improved by about 2 times, which can greatly improve the wind energy utilization rate and the turbine output power. The multi-blade design improves the low-speed heavy-load starting capability (such as a load-driven electric hydraulic pump).

[0078] 4-blade design can be 0.707 of the 2-blade length, so the 4-blade design can occupy less space, the RAT cabin door opening size is smaller, and the influence on the aircraft structure is minimal.

[0079] Therefore, the present application provides a ram air turbine emergency power driving device for an aircraft emergency power source, by arranging two groups of turbine blades, for example, two groups of turbine blades arranged coaxially in the axial direction in the initial state (for example, arranged front and back), the number of blades can be increased without affecting the space inside the ram air turbine cabin. In this way, the turbine starting speed is faster, and the RAT grid access time can be reduced. In addition, by increasing the number of blades, the efficiency of converting wind energy into energy by the turbine can also be improved, thereby improving the emergency power generation efficiency.

[0080] As a non-limiting example, the device can have multiple groups of turbine blades, for example, two groups of turbine blades. For example, in the initial state or position, the two groups of turbine blades are arranged front and back in the axial direction, for example, coaxially arranged. After being ejected outside the cabin, under the action of wind, the two groups of turbines can rotate relative to each other, thereby being connected as a four-blade turbine. Such a multi-blade turbine can improve the efficiency of converting wind energy into energy, power generation efficiency, and reduce the RAT grid access time.

[0081] Figure 2 is a schematic view of a ram air turbine emergency power driving device 100 according to a non-limiting embodiment of the present application in a first position, and Figure 3 is a schematic view of a ram air turbine emergency power driving device 100 according to a non-limiting embodiment of the present application in a second position.

[0082] According to the present application, the first position (or state) can be a position in which the ram air turbine is stowed inside the aircraft, in which the ram air turbine is not working. The second position (or state) can be a position in which the ram air turbine has been ejected outside the aircraft and has been rotated into place, in which the ram air turbine is ready to start working or is working.

[0083] As shown in the figures and according to a non-limiting embodiment, the ram air turbine emergency power driving device 100 can include a first group of turbine blades 10 and a second group of turbine blades 20 arranged coaxially in the axial direction A. For example, the second group of turbine blades 20 can be arranged in front of the first group of turbine blades 10, facing the ram air flow. In the example shown in the figures, the first group of turbine blades 10 and the second group of turbine blades 20 can each include two turbine blades arranged in a straight line. Each turbine blade can be the same size and shape, and the surface of the turbine blade has a predetermined deflection angle to rotate in a predetermined direction under the action of ram air.

[0084] As shown, in the first position, the first set of turbine blades 10 is stacked with the second set of turbine blades 20, for example, in a one in front of the other alignment, so as to minimize the space required for stowing and releasing.

[0085] In addition, although not shown in the drawings, the ram air turbine emergency power unit 100 can also be provided with a locking mechanism for locking the first set of turbine blades 10 with the second set of turbine blades 20 in the first position, so as to lock them in a position stacked on each other without interfering with the rest of the components, particularly during release from the cabin.

[0086] According to the present application, the second set of turbine blades 20 is able to rotate about the axial direction A from a first position (position shown in Figure 2 ) to a second position (position shown in Figure 3 ) relative to the first set of turbine blades 10 and remain in the second position, for example, after the locking device is unlocked. In the second position, the first set of turbine blades 10 and the second set of turbine blades 20 can be at a predetermined non-zero angle, for example, an angle of approximately 90 degrees as shown in Figure 3 .

[0087] The first set of turbine blades 10 can be fixed to the first mount 30, while the second set of turbine blades 20 can be fixed to the second mount 40. For example, the first mount 30 and the second mount 40 are coaxially mounted and can each have a hub-like structure and can be substantially hollow inside. Two blades of the first set of turbine blades 10 can extend from the side of the first mount 30 so as to be arranged in line. Likewise, the blades (for example, two blades) of the second set of turbine blades 20 can extend from the side of the second mount 40 so as to be arranged in line.

[0088] According to the present application, for simplicity, the combination of the first set of turbine blades 10 and the first mount 30 can be referred to as the first set of turbines, while the combination of the second set of turbine blades 20 and the second mount 40 can be referred to as the second set of turbines.

[0089] It should be understood that although the present application is described with reference to an embodiment in which each set of turbine blades includes two blades, a person skilled in the art can envisage other types of number and arrangement of blades without departing from the scope of the present application.

[0090] According to non-limiting embodiments of the present application, the first mount 30 and the second mount 40 can have a shape-complementary mating structure, such that in the second position, the first mount 30 and the second mount 40 are shape-fitted together, and at this time, such mating structure restricts the relative movement between the first mount 30 and the second mount 40, for example, restricts any circumferential movement therebetween, and for example, can restrict axial movement therebetween, together with the rest of the components or with the assistance of ram air.

[0091] Figure 4 is a schematic perspective view of another portion of the ram air turbine emergency power unit 100 according to the present application. Figure 5 is a schematic top view of a portion of the ram air turbine emergency power unit 100 according to the present application; and Figure 6 is a schematic perspective view of another portion of the ram air turbine emergency power unit 100 according to the present application.

[0092] As shown, as an example of the shape-complementary mating structure, the first mount 30 can include a first flange 31 and a first groove 32 (see Figure 4 ) spaced apart around the circumferential direction, while the second mount 40 includes a second flange 41 and a second groove 42 (see Figure 6 ) spaced apart around the circumferential direction. These flanges and grooves can be equally spaced apart from each other, such that each flange and groove approximately corresponds to a quarter of the circumference.

[0093] In this way, in the second position, the first flange 31 can be fitted into the second groove 42, and the second flange 41 can be fitted into the first groove 32, for example, such that the flanges and grooves are just snap-fitted together (as shown in Figure 3 ). With their snap-fitting, the axial distance between the first set of turbine blades 10 and the second set of turbine blades 20 also changes, such that they can be in the same rotational plane, to enhance the efficiency of the turbine in converting energy from wind power.

[0094] With continued reference to Figures 4 to 6 , the first flange 31 is provided with a first slide rail 31A in the form of a guide slot, while the first groove 32 is provided with a second slide rail 32A in the form of a guide slot (as shown in Figure 4 and 5 ). Correspondingly, the second flange 41 can be provided with a first slide block 41A, which for example, can protrude from the axial end of the second flange 41, and whose circumferential profile follows the shape of the second flange 41.

[0095] In this way, in the first position, the first slide block 41A can be fitted into the first slide rail 31A (as shown in Figure 2In the first position, the first slider 41A can fit into the first rail 31A (as shown in Figure 3

[0096] As a non-limiting example, after the RAT is released, the second set of turbines can first unlock the rotation, at which time the wind force acts on the turbines backwards. When the second flange 41 of the second set of turbines begins to enter the first groove 32 of the first set of turbines, the second set of turbines begins to move backwards within the first groove 32 under the action of the wind force (and possibly the biasing member). At the same time, the second flange 41 of the second set of turbines will bump into the sidewall of the first flange 31 of the first set of turbines during the rotation, so that the second flange 41 of the second set of turbines, the first slider 41A, and the first groove 32 of the first set of turbines, the second rail 32A, are completely coincided, and at the same time, the first flange 31 of the first set of turbines and the second groove 42 of the second set of turbines are coincided, so that the two sets of turbines are in the same horizontal rotation plane.

[0097] In this way, after the RAT is released in the air, the second set of turbine blades 20 begins to rotate, and under the action of the wind force (and possibly the biasing member), the second flange 41 of the second set of turbine blades can rotate into the first groove 32 of the first set of turbines, and the two sets of blades form four-blade turbine blades, as shown in Figure 3 This increases the number of rotating blades and improves the efficiency of utilizing wind energy.

[0098] It should be understood that although the present application describes the shape fitting way between the first mounting member 30 and the second mounting member 40 in the form of flanges and grooves, other types of structures that can achieve the shape fitting connection between them are also included in the scope of the present application. For example, structures with inclined slopes on each mounting member to wedge together, etc.

[0099] As clearly shown in Figure 4 The first rail 31A forms a through opening towards the end of the first flange 31 in the first circumferential direction B, and is closed at the opposite end to constrain the second mounting member 40 from rotating relative to the first mounting member 30 in the opposite direction, while allowing rotation in the first circumferential direction B. In addition, by this arrangement, the range of relative circumferential movement between the second mounting member 40 and the first mounting member 30 does not exceed the circumferential length of the first flange 31 or the second flange 41 when they are rotated relative to each other, because the closed end blocks the continued rotation of the second mounting member 40 relative to the first mounting member 30 in the first circumferential direction B. In this way, this structure only allows the second mounting member 40 to rotate relative to the first mounting member 30 from the first position to the second position, and remains in this second position, and cannot continue to rotate unless adjusted manually to return to the first position after use.

[0100] ​Figure 7 is a schematic cross-sectional view of a portion of a ram air turbine emergency power unit 100 according to the present application.

[0101] In Figure 7 the axial movement of the second mounting 40 relative to the first mounting 30 is shown. As shown and according to a non-limiting embodiment, the first mounting 30 can comprise a first shaft 30A, which can be integral with the first mounting 30 and can serve as a rotation axis to transmit the rotation of the blades to the gearbox or to the generator. The first shaft 30A is provided with a radial protrusion at the end thereof facing the second mounting 40, i.e. the right end in Figure 7

[0102] The second mounting 40 can comprise a housing 40A, which can be a substantially cylindrical structure and extends from the end face of the second mounting 40 towards the first mounting 30. The housing 40A is configured to guide the radial protrusion in the axial direction A, for example a piston-like guidance, to accommodate the axial movement of the second mounting 40 relative to the first mounting 30. The housing 40A is provided with a reduced diameter portion at the end thereof facing the first mounting 30, which can cooperate with the radial protrusion to prevent the first shaft 30A from coming out of the housing 40A.

[0103] In this way, in the first position, the radial protrusion can abut against the reduced diameter portion to limit the movement of the second mounting 40 in the axial direction A away from the first mounting 30, while in the second position, the radial protrusion can move from the reduced diameter portion to the end face of the second mounting 40 and abut against the end face or be spaced therefrom to allow the movement of the second mounting 40 in the axial direction A towards the first mounting 30, in turn axially moving from the first position to the second position and remaining in the second position.

[0104] Referring back to Figure 4 As shown, the ram air turbine emergency power unit 100 according to the present application can comprise a biasing member 50, which can be arranged around the first shaft 30A between the first mounting 30 and the second mounting 40. The biasing member 50 can be used to bias the second mounting 40 towards the first mounting 30 so as to cooperate the second mounting 40 with the first mounting 30 together, for example with the first flange 31 cooperating into the second groove 42 and the second flange 41 cooperating into the first groove 32, together with the action of the ram air during the deployment of the second set of turbine blades towards the second position.

[0105] ​Alternatively, the biasing member 50 can be used to bias the second mounting 40 away from the first mounting 30 so as to move the second set of mounting 40 away from the first set of mounting 30 when the ram air turbine emergency power unit 100 is not in operation, for example after the aircraft has landed, so as to facilitate its return to the first position for stowing the RAT. It will be appreciated that the biasing force at this time should be relatively small so as to enable the ram air force to move the second set of mounting 40 in the axial direction A towards the first mounting 30 when deployed to the second position.

[0106] In the embodiment shown in the drawings, the biasing member 50 is shaped in the form of a linear spring, but alternatively, in other embodiments, a person skilled in the art can provide the remaining types of biasing members, such as various elastomers (e.g. elastomeric composites, etc.).

[0107] The terms "front" and "rear" indicating the orientation or direction, and the terms "first", "second", etc. used to indicate the order as used herein are merely to make the person of ordinary skill in the art better understand the concept of the present application shown in the form of the preferred embodiment, and are not used to limit the present application. Unless otherwise stated, all orders, orientations or directions are only for the purpose of distinguishing one element / component / structure from another element / component / structure, and do not indicate any particular order, sequence of operation, direction or orientation unless otherwise stated. For example, in alternative embodiments, the "first set of turbine blades" can be the "second set of turbine blades", and the "first mounting" can alternatively refer to the "second mounting".

[0108] In summary, the ram air turbine emergency power unit 100 according to the embodiments of the present application overcomes the drawbacks in the prior art, and achieves the intended object of the present application.

[0109] Although the ram air turbine emergency power unit of the present application has been described above in conjunction with the preferred embodiments, it will be appreciated by those of ordinary skill in the art that the above examples are merely used to illustrate, and cannot be used as a limitation to the present application. Therefore, various modifications and variations can be made to the present application within the scope of the spirit of the claims, and these modifications and variations will all fall within the scope of the claims required by the present application.

Claims

1. A ram air turbine emergency energy drive device (100), comprising: A first set of turbine blades (10) and a second set of turbine blades (20) are coaxially arranged in an axial direction (A), wherein the second set of turbine blades (20) can be rotated relative to the first set of turbine blades (10) about the axial direction (A) from a first position to a second position and maintained in the second position, wherein, in the first position, the first set of turbine blades (10) overlaps the second set of turbine blades (20), and in the second position, the first set of turbine blades (10) is at a predetermined non-zero angle to the second set of turbine blades (20), The first group of turbine blades (10) is fixed to a first mounting member (30), and the second group of turbine blades (20) is fixed to a second mounting member (40), wherein the first mounting member (30) and the second mounting member (40) have a complementary matching structure, so that in the second position, the first mounting member (30) and the second mounting member (40) are matched together in shape and limit the movement of the second mounting member (40) relative to the first mounting member (30).

2. The ram air turbine emergency energy drive device (100) according to claim 1, characterized in that: The first mounting member (30) includes a first shaft (30A) having a radial protrusion at an end thereof facing the second mounting member (40), the second mounting member (40) including a receiving portion (40A), wherein the receiving portion is configured to guide the radial protrusion in the axial direction (A), and wherein the receiving portion has a reduced diameter portion at an end thereof facing the first mounting member (30).

3. The ram air turbine emergency energy drive device (100) according to claim 1, characterized in that: The first mounting member (30) includes a first flange (31) and a first groove (32) spaced apart around a circumferential direction, and the second mounting member (40) includes a second flange (41) and a second groove (42) spaced apart around the circumferential direction, wherein, in the second position, the first flange (31) fits into the second groove (42), and the second flange (41) fits into the first groove (32).

4. The ram air turbine emergency energy drive device (100) according to claim 3, characterized in that: The first flange (31) is provided with a first slide rail (31A), the first groove (32) is provided with a second slide rail (32A), and the second flange (41) is provided with a first slider (41A), wherein, in the first position, the first slider (41A) fits into the first slide rail (31A), and in the second position, the first slider (41A) fits into the second slide rail (32A).

5. The ram air turbine emergency energy drive device (100) according to claim 4, characterized in that: The first slide rail (31A) forms a through opening in a first circumferential direction (B) toward the end of the first flange (31), and is closed at the opposite end to constrain the second mounting member (40) to rotate relative to the first mounting member (30) only in the first circumferential direction (B).

6. The ram air turbine emergency energy drive device (100) according to claim 1, characterized in that: A biasing member (50) is provided between the first mounting member (30) and the second mounting member (40), the biasing member biasing the second mounting member (40) toward the first mounting member (30).

7. The ram air turbine emergency energy drive device (100) according to any one of claims 1 to 6, characterized in that: The first set of turbine blades (10) and the second set of turbine blades (20) each include two turbine blades arranged in a straight line.

8. The ram air turbine emergency energy drive device (100) according to any one of claims 1 to 6, characterized in that: In the second position, the first set of turbine blades (10) and the second set of turbine blades (20) are in the same rotational plane.

9. An aircraft comprising the ram air turbine emergency energy drive device (100) according to any one of claims 1-8.

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