• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    AIR FILTER SYSTEMS FOR AIR INPUTS OF AIRCRAFT ENGINES AND RELATED METHODS. Aircraft, methods and filter systems for air intakes for aircraft engines are described. An illustrative filter system includes a filter assembly having a first inner end defining an overflow opening, and a second end for coupling to an air inlet of an aircraft engine to allow incoming air from inside to enter the interior. air entrance. The filter assembly defines a substantially annular cross section and includes at least one filter means for removing contaminants from the incoming air entering the interior through the filter means. The filter system includes a mobile overrun enclosure with respect to the filter assembly between at least a first position and a second position.
    公开号:BR112014009067B1
    申请号:R112014009067-0
    申请日:2012-10-10
    公开日:2020-12-01
    发明作者:Mark Edward Boyce
    申请人:Aerospace Filtration Systems, Inc.；
    IPC主号:
    专利说明:

    CROSS REFERENCE TO RELATED ORDERS
    [001] This application claims the priority of U.S. non-provisional patent application No. 13 / 274,965 filed on October 17, 2011, the entire description of which is incorporated herein by reference in its entirety. FIELD
    [002] The field of this description generally refers to air filter systems for aircraft and related methods, and more particularly, filter systems for air intakes for aircraft engines and related methods. FUNDAMENTALS
    [003] This section is intended to introduce various aspects of the technique that can be related to various aspects of the present description, which are described and / or claimed below. This discussion should be useful in providing background information to facilitate better compression of the various aspects of the present description. These statements should be read from this perspective, and not as an admission of prior art.
    [004] An engine for aircraft propulsion requires the air intake to be free of contaminants to provide efficient combustion and prevent damage to internal engine components. Some known compressors and turbines are designed with small spaces between moving parts to maximize efficiency, but that also increases the vulnerability to damage to engine parts due to small foreign particles. Contamination of the inlet air, even in small quantities, can measure premature wear of engine components, increase maintenance costs, and degrade operational performance and reliability. The aircraft is exposed to contaminants when operating at low altitudes where the air is often contaminated with soil material, such as sand and dust. This problem can be exacerbated for helicopters due to the downward propulsion of the rotor and prolonged operation at low altitude. Systems that remove foreign particles from the intake stream are designed to protect the engine from damage. For example, a filter can be positioned through the motor inlet.
    [005] Filtered intake systems typically have an overflow port that provides an alternative air intake. During normal operations, the door remains closed and sealed to the alternate inlet to prevent contaminants from leaking into the filtered air stream. But if the contaminant separator becomes partially or totally restricted, the overtaking door is opened to allow greater air intake and safe engine operation. SUMMARY
    [006] In accordance with an aspect of the present description, a system filter is described. The filter system includes a filter assembly having a first inner end defining an overflow opening, and a second end for coupling to an air inlet of an aircraft engine to allow inlet air from the interior to enter the air inlet. of engine. The filter assembly defines a substantially annular cross section and includes at least one filter media to remove contaminants from the incoming air entering the interior through the filter media. The filter system includes a mobile overrun enclosure with respect to the filter assembly between at least a first position and a second position. The overflow enclosure substantially covers and substantially seals the overflow opening in the first position to inhibit the incoming air by preventing it from entering the interior through the overflow opening, and the overflow enclosure is spaced from the filter assembly in the second position to allow the incoming air enters the interior through the overflow opening. The filter system includes a driver coupled to at least one of the filter assembly and the override element to cause relative movement of the override enclosure between the first and second positions.
    [007] According to another aspect of this description, an aircraft is described. The aircraft includes a fuselage having a forward direction and an aircraft engine coupled to the fuselage. The aircraft engine includes at least one inlet that generally faces the forward direction for receiving incoming air. The aircraft includes a filter system including an overrun enclosure and a first set having an interior, a first end defining an overrun opening, and a second end coupled to the inlet to allow the incoming air flow from the inside of the overhead set filter inside the aircraft engine inlet. The filter assembly defines a substantially annular cross section. The overtaking area is mobile between a first position and a second position. The overflow enclosure substantially covers and substantially seals the overflow opening in the first position to prevent incoming air from entering through the overflow opening, and the overflow space spaced from the filter assembly in the second position to allow air of entry enter inside through the overflow opening.
    [008] In accordance with another aspect of this description, a method of reconditioning a filter assembly for an aircraft entry is described. The method includes removing a filter system associated with an aircraft engine air intake and attaching a replacement filter system to the aircraft engine air intake. The replacement filter system includes an overrun enclosure and a substantially cylindrical filter assembly having an interior and a first end defining an overrun opening. The overtaking area is mobile between a first position and a second position. The overflow enclosure substantially covers and substantially seals the overflow opening and the overflow enclosure is spaced from the filter assembly in the second position to allow inlet air to enter the interior through the overflow opening.
    [009] Several refinements exist of the characteristics noted with respect to the aspects mentioned above. Additional features can also be incorporated into the aspects mentioned above as well. These refinements and additional features can exist individually or in any combination. For example, several features discussed below with respect to any of the illustrated modalities can be incorporated into any of the aspects described above, alone or in any combination. BRIEF DESCRIPTION OF THE DRAWINGS
    [010] The drawings are not to scale and certain characteristics may be exaggerated to facilitate the illustration. Figure 1 is a perspective view of an aircraft according to an illustrative embodiment of the present description; Figure 2 is an exploded perspective view of an illustrative filter system; Figure 3 is a front perspective view of the assembled filter system of Figure 2; Figure 4 is a rear perspective view of the filter system of Figure 3; Figure 5A is an elevation view of the filter system of Figure 2, with an overtaking enclosure in a closed position; Figure 5B is an elevation view of the filter system of figure 3, with an overtaking enclosure in an open position; Figure 6 is a perspective view of a cross section of the filter assembly of Figure 4, along line 6-6; Figure 7 is an elevation view of the cross section of the filter assembly of Figure 4, along line 6-6; Figure 8 is a block diagram of a method of reconditioning a filter system according to another illustrative embodiment. DETAILED DESCRIPTION
    [011] Figure 1 illustrates a modality of an aircraft 100, and in that modality, the aircraft is a helicopter. Helicopters designated S-61, SH3, BV-107, CH-46, AS 332, Super Puma, MI-17, KA-27 and / or KA-32, CH-47 are just a few examples of helicopters used with the systems and methods of the present description.
    [012] Helicopter 100 generally includes a fuselage 102, rotor blades 104, and an aircraft engine 106, which may include a turbine engine, piston engine, or other type of engine suitable for generating blade rotation. rotor 104, which provides propulsion for aircraft 100. Fuselage 102 defines a forward direction 108, as shown in figure 1. Aircraft engine 106 includes two inlets 110a and 110b for receiving airflow for use by the engine of aircraft 106 in a combustion process. It must be appreciated that other helicopter modes may include a different number of inlets to receive the incoming air used in a combustion process. In this embodiment, the inlet 110 generally faces the forward direction 108, so that the forward movement of the helicopter 100 causes the inlet air to flow into the inlet 110.
    [013] Previous filter systems for helicopters include those illustrated in U.S. patents by the same assignee Nos. 6,595,742; 6,824,582; 7,192,462; 7,491,253; and 7,575,014, all of which are incorporated herein by reference.
    [014] As illustrated in figure 1, helicopter 100 includes two filter systems 112a, 112b. It should be appreciated that other helicopter modes may include a different number of filter sets. Each of the filter systems 112a-b being coupled to a respective input among the inputs 110a-110b. The incoming air passes through the filter system 112 before entering the air intake 110 of the aircraft engine 106. The filter system 112 is structured to filter the incoming air to remove contaminants from it, before allowing the inlet air enter the air inlet 110 of the aircraft engine 106. An illustrative filter system 112 is illustrated in figures 2 to 7.
    [015] The filter system 112 includes a filter assembly 114, which defines a substantially annular cross section. More particularly, in this illustrative embodiment, the filter assembly 114 includes a cylindrical filter assembly, as shown in Figure 4. It is contemplated that the filter assembly 114 can be substantially cylindrical, so that the filter assembly 114 defines a cylinder or defines a shape substantially consistent with a cylinder.
    [016] As shown in figure 4, filter assembly 114 has an interior 116. Filter assembly 114 includes a first end 118 and a second end 120. The first end 118 defines an overflow opening 122 (shown in figures 1 and 6 and 7), and the second end 120 is configured to couple with the air inlet 110 of the aircraft engine 106 to allow the inlet air from inside 116 to enter the air inlet 110. More specifically, the second end 120 of the filter assembly 114 is mounted on the engine of the aircraft 106, with the intake 110 received at least partially within the second ex-train 120, so that the inlet air inside 116 flows to the intake 110 during operation.
    [017] Filter set 114 includes filter means 124 arranged at least partially around a circumference of first set 114 to remove contaminants from the incoming air entering the interior 116 through filter means 124. As it should be apparent, a variety of configurations (for example, size, shape, number of elements, orientation, etc.) of filter medium 124 can be included in the modalities of the filter system. In that particular embodiment, filter means 124 includes filter elements 126, 127 and 128. Each filter element 126, 127, 128 defines a particle removal efficiency, for example, of at least about 97%, for particles from 5 to 80 microns. As such, filter elements 126, 127, 128 are configured to remove particulate contaminants from the incoming air, including sand and / or dust, which can prevail in various operating environments for the helicopter 100.
    [018] In the illustrative embodiment, the filter system 112 includes an override enclosure 130, which is arranged adjacent to the filter assembly 114. The overpass enclosure 130 is movable with respect to the filter assembly 114 between a first position and a second position. Specifically, in the first position, the overflow enclosure 130 substantially covers and substantially seals the overflow opening 122 of the filter assembly 114. Conversely, in the second position, the overflow enclosure 130 is spaced from the filter assembly 114, as shown in the figure 5B. In this embodiment, the enclosure 130 moves axially along a central geometric axis of the filter assembly and a central geometric axis of the enclosure.
    [019] As illustrated, overtaking area 130 is a substantially dome-shaped enclosure. Thus, when helicopter 100 is in flight, overtaking 130 provides reduced air resistance compared to one or more other formatted overtaking spaces. It should be appreciated, however, that an overrun enclosure can define any suitable shape, size and / or orientation to substantially cover override opening 122 of filter assembly 114, regardless of its air resistance during flight.
    [020] The filter system 112 additionally includes a driver 132 (as illustrated in figure 6) coupled between the overtaking 130 and the filter assembly 114 to cause relative movement of the overtaking between the first and second positions. In this embodiment, the driver 132 is mounted on the filter set 114 and connected to the override 130 to move override 130. In other embodiments, the driver can be mounted on the override 130 and coupled to the filter set 114 to move filter assembly 114. Actuator 132 may include an electric actuator, fluid actuator, pneumatic actuator or other suitable device to cause relative movement between filter assembly 114 and override 130. Consideration should be given to that a different number of actuators arranged in one or more different locations can be included in other types of filter set. Additionally, in this illustrative embodiment, the actuator is arranged in a center defined by an annular cross section of the filter assembly 114, in order to apply a balanced force to the overtaking area 130. Note that the cross section can also simply be a closed cross section, rather than a circular or annular cross section. Actuator 132, however, can be positioned differently in other embodiments.
    [021] The relative axial movement of override 130 and filter assembly 114 is provided by a suitable mechanism such as a plurality of hinges 134 coupled between override 130 and filter assembly 114. The plurality of hinges 134 includes eight hinges 134a-h coupled between the override and the filter assembly. As best illustrated in Figure 7, the eight joints 134a-h include four pairs of joints equally distributed around a circumference or overtaking area 130. The homogeneous distribution of the joints 134 allows for balanced movement between the overtaking area 130 and the filter assembly 114. In some embodiments, however, hinges 134 may otherwise be distributed to one or more different locations. While the hinges 134 are illustrated as separate and independent, it should be understood that two or more hinges 134 can be coupled together to provide rigidity to the relative movement between the override 130 and the filter assembly 114. Additionally, it is appreciated that a different number of joints 134 (including one joint) can be included in other modalities. In addition, a stabilizer, such as stabilizer bars, can be added to provide additional stiffness to the joints. In at least one embodiment, the hinges 134 can be omitted from the filter system 112. In such an embodiment, multiple actuators can cause and / or provide relative movement between the override 130 and the filter assembly 114.
    [022] In use, the inlet air enters the interior 116 of the filter assembly 114 in order to enter the inlet 110. The inlet air can enter the interior 116 through the filter means 124 and / or the overflow opening 122 , depending on the position of the override 130. More specifically, when the override 130 is arranged in the first position, that is, a closed position, the inlet air enters the interior 116 of the filter assembly 114 through the filter means 124. In this way, the incoming air is filtered for contaminants, before entry 110 of the aircraft engine 106.
    [023] Due to one or more reasons, the filter medium 124 may become restricted (for example, due to an accumulation of dust, sand or ice, etc.) during the operation of the helicopter 100, so that the pressure of the inlet air entering through filter means 124 is reduced. The reduction in the inlet air pressure can be detected by one or more sensors arranged near the filter medium 124. In response to the reduction in the inlet air pressure and / or an operator command, the actuator 132 is operated to move the override 130 from the first position to the second position, where the override 130 is spaced from the filter assembly 114, as shown in figure 6. As a result, the inlet air can enter the interior 116 of the filter assembly 114 through the overflow opening 122. Since the overflow opening 122 bypasses the filter medium 124, the additional inlet air can flow into the interior 116, and ultimately into the inlet 110 of the aircraft engine 106. Thus , filter means 124 reduces the amount of contaminants entering entry 110, thereby protecting aircraft engine 106 from damage, and also provides override 130 to bypass filter means 124 when determined by reduced intake air and / or an operator.
    [024] As illustrated in Figure 7, aircraft 100 includes a controller 136 to control one or more functions of aircraft 100. Controller 136 may include, for example, a full authority digital engine control (FADEC). In this illustrative embodiment, driver 132 is coupled to and responds to controller 136. More specifically, in one example, aircraft 100 includes an entry (not shown) for an operator of aircraft 100 to command overtaking 130 through controller 136 , to move between the first and second positions. The entry may include, without limitation, a button, a switch, a dial and / or a button, etc., arranged within an aircraft 100 flight deck that is accessible to an aircraft operator 100. When the operator registration is accelerated, controller 136 commands driver 132 to cause relative axial movement from overtaking 130 to the first or second position as requested by the aircraft operator 100.
    [025] Additionally, or alternatively, controller 136 can respond to one or more sensors (not shown) located near filter medium 124. In at least one embodiment, the sensors are located to detect air pressure inside the interior 116 to determine if sufficient inlet air is entering through filter medium 124. If insufficient inlet air is entering through filter medium 124 (indicating that filter medium 124 is restricted and / or covered with ice), the controller 136 can automatically command driver 132 to move override 130 to the second position, thus allowing incoming air to enter through overpass passage 122. Alternatively, controller 136 can provide an indication of the air pressure of reduced entry for the operator of aircraft 100, and waiting for command from an operator as described above. Overtaking 130 can be triggered between first and second positions for several reasons, with respect to, without limitation, safety and performance.
    [026] In the illustrative mode, the filter system 112 includes a foreign object residue (FOD) screen 138 positioned to filter the incoming air entering the interior through the overflow opening. As illustrated in figures 1 and 6 to 7, the FOD 138 screen is arranged at least partially inside the overflow opening 122. More specifically, the FOD 138 screen is arranged to filter the incoming air entering through the overflow opening 122, but do not filter and / or inhibit the incoming air flow entering the interior 116 through the filter medium 124. In contrast to the filter medium 124, the FOD 138 screen is significantly more porous than the filter medium. For example, the FOD 138 screen defines a 1/4 "by 1/4" stainless steel interlacing in this illustrative mode. It must be appreciated, however, that the FOD 138 screen may include a different configuration (for example, size, shape, interlacing, etc.) and / or be positioned elsewhere in other modalities of the filter set. In at least one mode, the FOD 138 screen can be omitted.
    [027] The filter system 112 includes an elastomeric seal 139 coupled to the override enclosure 130. The elastomeric seal 139 is configured so that when the override enclosure 130 is arranged in the first position, a seal is formed between the overflow enclosure overflow 130 and filter assembly 114 to prevent inlet air from entering the interior 116 of filter assembly 114 through overflow opening 122. It should be appreciated that the seal can be arranged elsewhere and / or made a variety of materials, possibly depending on one or more environments, where the aircraft 100 should operate. In some instances, the elastomeric seal 139 may be coupled to the filter assembly 114 and arranged to contact override 130, when disposed in the first position.
    [028] Referring again to figure 3, filter system 112 includes three mounting brackets 142a-c. Each of the mounting brackets 142 is structured to be mounted on the air inlet 110 of the aircraft engine 106 to support the filter system 112 with respect to the aircraft engine 106. In the particular embodiment, the brackets 142 are configured to allow the air inlet 110 is at least partially received at the second end 120 of filter assembly 114. It should be apparent that a different number and / or configuration (for example, size, shape, position, etc.) of the supports 142 can be used in other arrangements for mounting the filter system 112 to the aircraft engine 106, potentially depending on the aircraft 100 in which the filter system 112 is included. In at least one embodiment, the supports 142 can include multiple mounting openings, so that the filter system 112 is universal for multiple types of aircraft 100.
    [029] Figure 8 illustrates a method 200 of reconditioning a filter system according to another illustrative embodiment. While method 200 is described with reference to aircraft 100 and filter system 112, it should be appreciated that method 200 can be employed to retroactively fit a variety of different aircraft and / or filter systems, and therefore does not is limited to aircraft 100 and / or filter system 112 illustrated in figures 1 to 7. Likewise, aircraft 100 and filter system 112 described above are not limited to the method described with reference to figure 8.
    [030] In the illustrative embodiment, method 200 includes removing 202 of a filter system associated with an air inlet 110 of an aircraft engine 106 and coupling 204 of a replacement filter system 112 for air inlet 110 of the aircraft engine 106. The replacement filter system 112 includes the override 130 and the substantially cylindrical filter assembly 114 having the interior 116 and a first end 118 defining an override aperture 122. As described above, the override enclosure 130 is movable between a first position and a second position.
    [031] In some embodiments, method 200 may include coupling the driver 132 to a controller 136, the controller configured to provide an override command for the driver to control the movement of the override enclosure between the first and second positions in response at least one of the operator log and an inlet air condition.
    [032] When introducing elements of the present invention or modalities, the articles "one", "one", "o", "a" and "said", "said" must mean that there are one or more of the elements. The terms "comprising", "including", and "possessing" must be inclusive and mean that there may be additional elements in addition to the elements listed.
    [033] Since several changes can be made to the above constructions without departing from the scope of the invention, it is intended that all the matter contained in the description above and illustrated in the attached drawings should be interpreted as illustrative and not in a limiting sense.
    权利要求:
    Claims (19)
    [0001]
    1. Filter system (112) for an air intake (110) of an aircraft engine (106), said filter system (112) CHARACTERIZED by the fact that it comprises: a filter assembly (114) having an interior (116), a first end (118) defining an overflow opening (122) and a second end (120) for coupling to an air inlet (110) of an aircraft engine (106) to allow the incoming air from inside (116) enter the air inlet (110), the filter assembly (114) defining a substantially annular cross section and including at least one filter means (124) to remove contaminants from the incoming air entering the interior ( 116) through the filter means (124); a override (130) movable with respect to the filter assembly (114) between at least a first position and a second position, the override (130) substantially covering the override opening (122) in the first position to inhibit air inlet (116) through the overflow opening (122), the overflow enclosure (130) spaced from the filter assembly (114) in the second position to allow the inlet air to enter the interior (116) through the overtaking opening (122); and a driver (132) coupled to at least one of the filter assembly (114) and the override element to cause relative movement of the override enclosure (130) between the first and second positions.
    [0002]
    2. Filter system (112) according to claim 1, CHARACTERIZED by the fact that the overtaking enclosure (130) includes a substantially domed overtaking enclosure (130).
    [0003]
    3. Filter system (112), according to claim 1, CHARACTERIZED by the fact that the overtaking area (130) is axially mobile with respect to the filter set (114).
    [0004]
    4. Filter system (112) according to claim 1, CHARACTERIZED by the fact that it additionally comprises a plurality of joints (134) coupled between the filter assembly (114) and the overtaking area (130) to allow the axial movement between the filter assembly (114) and the overtaking enclosure (130).
    [0005]
    5. Filter system (112), according to claim 1, CHARACTERIZED by the fact that it additionally comprises a foreign object residue (FOD) screen (138) positioned to filter the incoming air that enters the interior (116) filter assembly (114) through the overflow opening (122).
    [0006]
    6. Filter system (112) according to claim 1, CHARACTERIZED by the fact that one of the overtaking enclosure (130) and the filter assembly (114) includes an elastomeric seal (139) to contact the other of the enclosure bypass (130) and the filter assembly (114) to inhibit the entry of inlet air into the interior (116) of the filter assembly (114) through the overflow opening (122) when the overflow enclosure (130) is first position.
    [0007]
    7. Filter system (112) according to claim 1, CHARACTERIZED by the fact that the actuator (132) is mounted on the filter assembly (114) substantially at a center defined by the annular cross section of the filter assembly (114 ).
    [0008]
    8. Aircraft (100), CHARACTERIZED by the fact that it comprises: a fuselage (102) having a forward direction (108); an aircraft engine (106) coupled to the fuselage (102), the aircraft engine (106) including at least one inlet (110) generally facing the forward direction (108) to receive inlet air; and a filter system (112) including an override enclosure (130) and a filter assembly (114) having an interior (116), a first end (118) defining an override opening (122), and a second end (120) coupled to the inlet (110) to allow air flow from the inlet (116) of the filter assembly (114) into the inlet (110) of the aircraft engine (106), the filter assembly (114 ) defining a substantially annular cross section; wherein the overtaking area (130) is movable between a first position and a second position, the overtaking area (130) substantially covering the overtaking opening (122) in the first position to inhibit incoming air from entering the interior (116 ) through the overflow opening (122), the overflow enclosure (130) spaced from the filter assembly (114) in the second position to allow inlet air to enter the interior (116) through the overflow opening (122).
    [0009]
    9. Aircraft (100), according to claim 7, CHARACTERIZED by the fact that the aircraft (100) is a helicopter.
    [0010]
    10. Aircraft (100), according to claim 8, CHARACTERIZED by the fact that the overtaking area (130) is axially mobile with respect to the filter assembly (114).
    [0011]
    11. Aircraft (100), according to claim 9, CHARACTERIZED by the fact that it additionally comprises an actuator (132) coupled to the overtaking element and the filter assembly (114), the actuator (132) operating to move the element overtaking between the first and second positions in response to an overtaking command.
    [0012]
    12. Aircraft (100), according to claim 10, CHARACTERIZED by the fact that the override command is based on at least one of a pressure differential between the inside and outside of the filter assembly (114) and a operator input.
    [0013]
    13. Aircraft (100), according to claim 10, CHARACTERIZED by the fact that the filter assembly (114) includes a foreign object waste (FOD) screen (138) positioned inside the interior (116) of the filter assembly (114) to filter at least the incoming air received through the overflow opening (122).
    [0014]
    14. Aircraft (100) according to claim 10, CHARACTERIZED by the fact that the filter system (112) includes a plurality of joints (134) coupled between the filter assembly (114) and the overtaking area (130 ) to allow axial movement between the filter assembly (114) and the overtaking area (130).
    [0015]
    15. Aircraft (100) according to claim 14, CHARACTERIZED by the fact that the plurality of joints (134) includes four pairs of joints (134) distributed substantially homogeneously around a circumference of the filter assembly (114 ).
    [0016]
    16. Aircraft (100), according to claim 10, CHARACTERIZED by the fact that the overtaking area (130) includes a substantially dome overtaking area (130).
    [0017]
    17. Aircraft (100) according to claim 16, CHARACTERIZED by the fact that the filter assembly (114) includes a filter means (124) arranged at least partially around a circumference of the filter assembly (114) substantially cylindrical to remove contaminants from the incoming air entering the interior (116) through the filter medium (124), the filter medium (124) including at least two segments of filter medium (124).
    [0018]
    18. Method of reconditioning a filter system (112) for an air intake (110) of an aircraft engine (106), said method CHARACTERIZED by the fact that it comprises: removing a filter system (112) associated with an air intake (110) of an aircraft engine (106); and coupling a replacement filter system (112) to the air intake (110) of the aircraft engine (106), the replacement filter system (112) including an override enclosure (130) and a substantially cylindrical filter assembly (114) having an interior (116) and a first end (118) defining an overtaking opening (122), the overtaking space (130) movable between a first position and a second position, the overtaking space (130) covering substantially the overflow opening (122) in the first position to prevent inlet air from entering the interior (116) through the overflow opening (122), the overflow enclosure (130) spaced from the filter assembly (114) in the second position for allow the inlet air to enter the interior (116) through the overflow opening (122).
    [0019]
    19. Method, according to claim 18, CHARACTERIZED by the fact that the replacement filter system (112) includes a driver (132) operated to move the overtaking area (130) between the first and second positions; and further comprises coupling the driver (132) to a controller, the controller (136) configured to provide an override command for the driver (132) to control the movement of the override enclosure (130) between the first and second positions in response to at least one of an operator inlet and an inlet air condition.
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    同族专利:
    公开号 | 公开日
    US8961634B2|2015-02-24|
    US20130092798A1|2013-04-18|
    EA201400474A1|2014-09-30|
    EA029974B1|2018-06-29|
    BR112014009067A2|2017-04-18|
    EP2768600A2|2014-08-27|
    WO2013103416A3|2013-08-29|
    WO2013103416A2|2013-07-11|
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    法律状态:
    2018-03-27| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-08-13| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-07-07| B09A| Decision: intention to grant|
    2020-12-01| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 10/10/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/274,965|US8961634B2|2011-10-17|2011-10-17|Filter systems for air intakes of aircraft engines and related methods|
    US13/274,965|2011-10-17|
    PCT/US2012/059460|WO2013103416A2|2011-10-17|2012-10-10|Filter systems for air intakes of aircraft engines and related methods|
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