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WO2007090011A2 - Engine air intake barrier filter system for aircraft - Google Patents

Engine air intake barrier filter system for aircraft Download PDF

Info

Publication number
WO2007090011A2
WO2007090011A2 PCT/US2007/060910 US2007060910W WO2007090011A2 WO 2007090011 A2 WO2007090011 A2 WO 2007090011A2 US 2007060910 W US2007060910 W US 2007060910W WO 2007090011 A2 WO2007090011 A2 WO 2007090011A2
Authority
WO
WIPO (PCT)
Prior art keywords
filter
aircraft
filter element
filter system
media
Prior art date
Application number
PCT/US2007/060910
Other languages
French (fr)
Other versions
WO2007090011A3 (en
Inventor
Joseph L. Wilson
Original Assignee
Aerospace Filtration Systems, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aerospace Filtration Systems, Inc. filed Critical Aerospace Filtration Systems, Inc.
Publication of WO2007090011A2 publication Critical patent/WO2007090011A2/en
Publication of WO2007090011A3 publication Critical patent/WO2007090011A3/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D46/00—Filters or filtering processes specially modified for separating dispersed particles from gases or vapours
    • B01D46/0002—Casings; Housings; Frame constructions
    • B01D46/0005—Mounting of filtering elements within casings, housings or frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D46/00—Filters or filtering processes specially modified for separating dispersed particles from gases or vapours
    • B01D46/10—Particle separators, e.g. dust precipitators, using filter plates, sheets or pads having plane surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D46/00—Filters or filtering processes specially modified for separating dispersed particles from gases or vapours
    • B01D46/52—Particle separators, e.g. dust precipitators, using filters embodying folded corrugated or wound sheet material
    • B01D46/521—Particle separators, e.g. dust precipitators, using filters embodying folded corrugated or wound sheet material using folded, pleated material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D2275/00—Filter media structures for filters specially adapted for separating dispersed particles from gases or vapours
    • B01D2275/20—Shape of filtering material
    • B01D2275/203—Shapes flexible in their geometry, e.g. bendable, adjustable to a certain size
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/022—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising bird or foreign object protections

Definitions

  • the present invention is directed to barrier filter systems, and more particularly to barrier filter systems for filtering intake air of aircraft engines.
  • Filter systems typically comprise a replaceable filter assembly including a rigid retention frame installed around the filter media. After a period of use, the filter assembly is removed from the aircraft, cleaned, and then reinstalled in the aircraft.
  • the rigid frame around the filter media is useful because it helps ensure that the media will maintain its shape, even under the high air flow in the air intake stream of an aircraft.
  • the rigid frame may also facilitate, among other things, storage and cleaning of the filter.
  • the prior art filter assembly is relatively expensive, due at least in part to the rigid frame. Additionally, if the filter assembly must be curved to conform to the aircraft, special tooling is required to manufacture the filter element.
  • One aspect is directed to an inlet barrier filter element for mounting on an aircraft for filtering air prior to intake into an engine of the aircraft.
  • the filter element comprises flexible filter media and a WSTR 8483.1 PCT
  • the filter element is generally flat prior to installation and is capable of bending upon mounting on the aircraft to conform to the aircraft.
  • an inlet barrier filter system is mounted on an aircraft and is disposed for filtering air prior to intake into an engine of the aircraft.
  • the filter system generally comprises a filter element including filter media and having a flexible border.
  • a rigid frame is mounted on the aircraft.
  • the filter element is sized and shaped to be received in the rigid frame.
  • a retainer system is mountable on the frame for retaining the filter element after it is installed in the frame .
  • FIG. 1 is a perspective, partially cut-away view of a portion of an example helicopter including one embodiment of a filter system.
  • Fig. 2 is an exploded view of the filter system.
  • FIG. 3 is a section view of a retainer system of one embodiment.
  • FIG. 4 is a perspective view of a filter element of the system.
  • an inlet barrier filter system 11 of one embodiment is mounted in an aircraft engine air inlet 12.
  • the type of aircraft and engine is not important to this invention, but the aircraft shown is a portion of a helicopter 13 having a jet engine 15.
  • the system 11 is disposed for filtering air prior to intake into the engine to inhibit harmful particles from contacting and thereby damaging the engine.
  • the system is disposed in the air inlet, though other configurations are contemplated within the scope of the invention.
  • the filter system 11 generally comprises a flexible filter element 21, a rigid frame 23, and a retainer system 25.
  • the flexible filter element 21 includes a suitable filter media 31.
  • the filter media 31 is capable of achieving high particle removal efficiencies.
  • the media has a face velocity range of between 15 to 50 feet per second (fps) .
  • the pressure drop across the media will range from .6 inches of water at 15 fps to 5.6 inches of water at 50 fps.
  • the filter media 31 is suitably made of a lightweight material that will also be resistant to damage by water and other liquids it may encounter in operation.
  • Suitable filter media includes paper, woven cotton, WSTR 8483.1 PCT
  • the media may include a grid fabric having a plurality of layers.
  • the filter media 31 may be strengthened by a stainless steel screen (not shown) which encloses all or a portion of the filter media.
  • the filter media 31 may be impregnated with oil that not only improves particle removal, but also helps resist moisture absorption by the filter media rendering it waterproof.
  • the media of this embodiment is also pleated.
  • Various other configurations, including other filter media and unpleated media are contemplated within the scope of the invention .
  • the filter element 21 has a flexible border 35 attached around the outer edges or border of the media 31.
  • the flexible border 35 includes a potting material, e.g., a polysulphite, polyurethane or other polymeric, or an epoxy, among other suitable materials.
  • the potting material helps to seal the border around the filter element 21 and forms a perimeter to facilitate mounting, e.g., the installer can grasp the filter element by the potting material and install it in the aircraft.
  • Other materials for the border are contemplated.
  • the filter element 21 of this embodiment is generally planar or flat as manufactured and prior to installation.
  • the element can be manufactured using inexpensive tooling (not shown) that is generally flat or planar. In other words, the manufacturing process, and the tooling used therein, does not impart any curvature to the filter element. The manufacturing process is therefore easier and less expensive .
  • WSTR 8483.1 PCT
  • the potting material can be attached or formed around the filter media 31 in the tooling.
  • the flexible filter element can be deflected or bent significantly to conform to the aircraft.
  • the element 21, or portions thereof can be bent or flexed to a radii of less than 20 inches, and in other embodiments flexed even further to less than 15 inches or even less than 10 inches in radius.
  • the rigid frame 23 that receives the filter element 21 is suitably mounted on the helicopter 13 (it may be original equipment or retrofit on existing aircraft, and can take a variety of configurations) .
  • the frame 23 includes a plurality of border members 41 (e.g., four as shown) that support the border 35 of the filter element 21.
  • the cross-section (Fig. 3) of each border member 41 includes a wall 43, a flange 45 extending perpendicularly therefrom, and a small inwardly turned lip 47.
  • the frame 23 can include cross-members 49 (giving it a "window pane" look) .
  • the border members 41 may be formed separately, or integrally as one piece.
  • the retainer system 25 of this embodiment includes a retainer plate 51 having an inwardly turned lip 53 extending from the plate.
  • the wall, flange, plate and the respective lips of this embodiment retain or capture the border 35 of the filter element 21.
  • the system 25 also includes suitable fasteners 55, e.g., screws, extending through respective holes 57 in the plate 51 and the border members 41 of the frame 23.
  • suitable fasteners 55 e.g., screws
  • a small seal 61 extends along the flange 45 of this embodiment to facilitate sealing around the border 35 of the element 21.
  • the seal is designed so that the filter element can be readily removed from the frame without damage.
  • the seal may be a light adhesive applied between the border members and the border 35 of the filter element 21. The adhesive is light enough to allow for easy removal of the filter element 21.
  • the seal may also form part of the retainer system 25.
  • the frame 23 of this embodiment is adjacent the contour or outer moldline 65 of the aircraft.
  • the rigid frame 23 and retainer plate 25 of this embodiment are curved to conform to the moldline 65.
  • the filter element 21, and especially the border 35 of the filter element is flexible to conform to the curve.
  • the filter element 21 is resilient as well.
  • the filter system 11 of this embodiment conforms to the outer moldline 65 of the helicopter 13, and the filter element 21 may form part of the outer moldline of the helicopter.
  • Other configurations are contemplated, including those where the border members are not curved and where the frame is located downstream in the air intake system so that it is not adjacent the moldline.
  • the filter element can be easily manufactured flat, and is also flexible so that it is capable of being installed in a curved frame on the aircraft.
  • the filter element is inexpensive because less expensive tooling may be used, thereby decreasing the cost of the filter element. If the filter element were manufactured in a curved but rigid configuration, the tooling required to WSTR 8483.1 PCT
  • the filter element is so inexpensive as to be "disposable", meaning that rather than cleaning the filter after it becomes dirty as has been the practice with prior art aircraft filters of this type, the filter is discarded without cleaning-
  • the filter element may also be cleaned or otherwise refurbished within the scope of this invention .

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Filtering Of Dispersed Particles In Gases (AREA)

Abstract

An inlet barrier filter system (11) is mountable on an aircraft (13) and is disposed for filtering air prior to intake into an engine of the aircraft. The filter system (11) generally includes a filter element (21) having filter media (31) and a flexible border (35). A rigid frame (23) may be mounted on the aircraft (13). The filter element (21) may be sized and shaped to be received in the rigid frame (23). A retainer system (25) may retain the filter element (21) after it is installed in the frame.

Description

WSTR 8483.1 PCT
ENGINE AIR INTAKE BARRIER FILTER SYSTEM FOR AIRCRAFT
FIELD OF THE INVENTION
[0001] The present invention is directed to barrier filter systems, and more particularly to barrier filter systems for filtering intake air of aircraft engines.
BACKGROUND OF THE INVENTION
[0002] Prior art barrier filter systems for aircraft are shown, for example, in co-assigned U.S. Pat. Nos. 6,595,742 and 6,824,582, and Pat. App . No. 10/823,934, all of which are incorporated herein by reference. Filter systems typically comprise a replaceable filter assembly including a rigid retention frame installed around the filter media. After a period of use, the filter assembly is removed from the aircraft, cleaned, and then reinstalled in the aircraft. The rigid frame around the filter media is useful because it helps ensure that the media will maintain its shape, even under the high air flow in the air intake stream of an aircraft. The rigid frame may also facilitate, among other things, storage and cleaning of the filter. However, the prior art filter assembly is relatively expensive, due at least in part to the rigid frame. Additionally, if the filter assembly must be curved to conform to the aircraft, special tooling is required to manufacture the filter element.
SUMMARY OF THE INVENTION
[0003] One aspect is directed to an inlet barrier filter element for mounting on an aircraft for filtering air prior to intake into an engine of the aircraft. The filter element comprises flexible filter media and a WSTR 8483.1 PCT
flexible border extending around the filter media. The filter element is generally flat prior to installation and is capable of bending upon mounting on the aircraft to conform to the aircraft.
[0004] In another aspect, an inlet barrier filter system is mounted on an aircraft and is disposed for filtering air prior to intake into an engine of the aircraft. The filter system generally comprises a filter element including filter media and having a flexible border. A rigid frame is mounted on the aircraft. The filter element is sized and shaped to be received in the rigid frame. A retainer system is mountable on the frame for retaining the filter element after it is installed in the frame .
[0005] Various refinements exist of the features noted in relation to the above-mentioned aspects of the present invention. Further features may also be incorporated in the above-mentioned aspects of the present invention as well. These refinements and additional features may exist individually or in any combination. For instance, various features discussed below in relation to any of the illustrated embodiments of the present invention may be incorporated into any of the above- described aspects of the present invention, alone or in any combination.
BRIEF DESCRIPTION OF THE DRAWINGS
[0006] Fig. 1 is a perspective, partially cut-away view of a portion of an example helicopter including one embodiment of a filter system.
[0007] Fig. 2 is an exploded view of the filter system. WSTR 8483.1 PCT
[0008] Fig. 3 is a section view of a retainer system of one embodiment.
[0009] Fig. 4 is a perspective view of a filter element of the system.
[0010] Corresponding reference characters indicate corresponding parts throughout the drawings .
DETAILED DESCRIPTION OF THE DRAWINGS
[0011] Referring to Figs. 1-3, an inlet barrier filter system 11 of one embodiment is mounted in an aircraft engine air inlet 12. The type of aircraft and engine is not important to this invention, but the aircraft shown is a portion of a helicopter 13 having a jet engine 15. The system 11 is disposed for filtering air prior to intake into the engine to inhibit harmful particles from contacting and thereby damaging the engine. In this embodiment, the system is disposed in the air inlet, though other configurations are contemplated within the scope of the invention. The filter system 11 generally comprises a flexible filter element 21, a rigid frame 23, and a retainer system 25.
[0012] The flexible filter element 21 includes a suitable filter media 31. In one embodiment, the filter media 31 is capable of achieving high particle removal efficiencies. In this embodiment, the media has a face velocity range of between 15 to 50 feet per second (fps) . The pressure drop across the media will range from .6 inches of water at 15 fps to 5.6 inches of water at 50 fps. The filter media 31 is suitably made of a lightweight material that will also be resistant to damage by water and other liquids it may encounter in operation. Suitable filter media includes paper, woven cotton, WSTR 8483.1 PCT
polyester or felt. The media may include a grid fabric having a plurality of layers. The filter media 31 may be strengthened by a stainless steel screen (not shown) which encloses all or a portion of the filter media. To improve the filter efficiency for finer particles, the filter media 31 may be impregnated with oil that not only improves particle removal, but also helps resist moisture absorption by the filter media rendering it waterproof. The media of this embodiment is also pleated. Various other configurations, including other filter media and unpleated media are contemplated within the scope of the invention .
[0013] The filter element 21 has a flexible border 35 attached around the outer edges or border of the media 31. In this embodiment, the flexible border 35 includes a potting material, e.g., a polysulphite, polyurethane or other polymeric, or an epoxy, among other suitable materials. The potting material helps to seal the border around the filter element 21 and forms a perimeter to facilitate mounting, e.g., the installer can grasp the filter element by the potting material and install it in the aircraft. Other materials for the border are contemplated.
[0014] As shown in Fig. 4, the filter element 21 of this embodiment is generally planar or flat as manufactured and prior to installation. The element can be manufactured using inexpensive tooling (not shown) that is generally flat or planar. In other words, the manufacturing process, and the tooling used therein, does not impart any curvature to the filter element. The manufacturing process is therefore easier and less expensive . WSTR 8483.1 PCT
[0015] The potting material can be attached or formed around the filter media 31 in the tooling. When the filter element is ready to be installed on the aircraft, the flexible filter element can be deflected or bent significantly to conform to the aircraft. In one embodiment, the element 21, or portions thereof, can be bent or flexed to a radii of less than 20 inches, and in other embodiments flexed even further to less than 15 inches or even less than 10 inches in radius.
[0016] The rigid frame 23 that receives the filter element 21 is suitably mounted on the helicopter 13 (it may be original equipment or retrofit on existing aircraft, and can take a variety of configurations) . In this embodiment, the frame 23 includes a plurality of border members 41 (e.g., four as shown) that support the border 35 of the filter element 21. More particularly, the cross-section (Fig. 3) of each border member 41 includes a wall 43, a flange 45 extending perpendicularly therefrom, and a small inwardly turned lip 47. Optionally, the frame 23 can include cross-members 49 (giving it a "window pane" look) . The border members 41 may be formed separately, or integrally as one piece.
[0017] The retainer system 25 of this embodiment includes a retainer plate 51 having an inwardly turned lip 53 extending from the plate. The wall, flange, plate and the respective lips of this embodiment retain or capture the border 35 of the filter element 21. The system 25 also includes suitable fasteners 55, e.g., screws, extending through respective holes 57 in the plate 51 and the border members 41 of the frame 23. However, many other configurations of the frame and retainer system are contemplated . WSTR 8483.1 PCT
[0018] A small seal 61 extends along the flange 45 of this embodiment to facilitate sealing around the border 35 of the element 21. The seal is designed so that the filter element can be readily removed from the frame without damage. Many other sealing configurations are contemplated. For example, the seal may be a light adhesive applied between the border members and the border 35 of the filter element 21. The adhesive is light enough to allow for easy removal of the filter element 21. The seal may also form part of the retainer system 25.
[0019] The frame 23 of this embodiment is adjacent the contour or outer moldline 65 of the aircraft. Thus, the rigid frame 23 and retainer plate 25 of this embodiment are curved to conform to the moldline 65. The filter element 21, and especially the border 35 of the filter element, is flexible to conform to the curve. In some cases, the filter element 21 is resilient as well. Thus, the filter system 11 of this embodiment conforms to the outer moldline 65 of the helicopter 13, and the filter element 21 may form part of the outer moldline of the helicopter. Other configurations are contemplated, including those where the border members are not curved and where the frame is located downstream in the air intake system so that it is not adjacent the moldline.
[0020] The filter element can be easily manufactured flat, and is also flexible so that it is capable of being installed in a curved frame on the aircraft. The filter element is inexpensive because less expensive tooling may be used, thereby decreasing the cost of the filter element. If the filter element were manufactured in a curved but rigid configuration, the tooling required to WSTR 8483.1 PCT
assemble the filter element would be significantly more expensive .
[0021] In some embodiments of the present invention, the filter element is so inexpensive as to be "disposable", meaning that rather than cleaning the filter after it becomes dirty as has been the practice with prior art aircraft filters of this type, the filter is discarded without cleaning- However, the filter element may also be cleaned or otherwise refurbished within the scope of this invention .
[0022] When introducing elements of various aspects of the present invention or embodiments thereof, the articles ""a", "an", "the" and "said" are intended to mean that there are one or more of the elements- The terms "comprising", "including" and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements. Moreover, the use of "top" and "bottom", "front" and "rear", "above" and "below" and variations of these and other terms of orientation is made for convenience, but does not require any particular orientation of the components.
[0023] As various changes could be made in the above constructions, methods and products without departing from the scope of the invention, it is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense. Further, all dimensional information set forth herein is exemplary and is not intended to limit the scope of the invention unless stated otherwise .

Claims

WSTR 8483.1 PCTWhat is claimed is:
1. An inlet barrier filter element for mounting on an aircraft for filtering air prior to intake into an engine of the aircraft, the filter element comprising flexible filter media and a flexible border extending around the filter media, wherein the filter element is generally flat prior to installation and capable of bending upon mounting on the aircraft to conform to the aircraft .
2. The filter system of claim 1 wherein the filter element is capable of bending to a radius less than 20 inches without damaging the element.
3. The filter system of claim 1 wherein the filter element can bend to a radius less than 10 inches without damaging the element.
4. The filter system of claim 1 wherein the media has a face velocity of from 15 to 50 feet per second.
5. The filter system of claim 1 wherein the media causes a pressure drop of no more than 0.6 to 5.6 inches of water.
6. The filter system of claim 1 wherein the flexible border includes flexible potting material.
7. The filter system of claim 1 wherein the filter element includes pleated cotton media. WSTR 8483.1 PCT
8. The filter system of claim 7 wherein the media is dry.
9. The filter system of claim 7 wherein the media is wet.
10. The filter system of claim 1 wherein the filter element includes pleated paper media.
11. An inlet barrier filter system mounted on an aircraft and disposed for filtering air prior to intake into an engine of the aircraft, the filter system comprising: a flexible filter element including flexible filter media and a flexible border around the media; a rigid frame mounted on the aircraft; and a retainer system for retaining the filter element in the frame ; wherein the flexible filter element flexes to conform to the rigid frame mounted on the aircraft.
12. The filter system of claim 11 wherein the filter element is bent to a radius less than 20 inches.
13. The filter system of claim 11 wherein the media has a face velocity of from 15 to 50 feet per second.
14. The filter system of claim 11 wherein the media causes a pressure drop of no more than 0.6 to 5.6 inches of water. WSTR 8483.1 10
PCT
15. The filter system of claim 11 wherein the rigid frame includes a plurality of border members for supporting the border of the element and includes cross- members extending between the border members for supporting areas of the filter element spaced from the border.
16. The filter system of claim 15 wherein at least two of the border members are curved, the filter element being flexible to conform to the curve.
17. The filter system of claim 11 wherein the frame is adjacent the outer moldline of the aircraft, and a resilient, curved outer surface of the filter element conforms to the outer moldline.
18. The filter system of claim 11 in combination with the aircraft and wherein the aircraft is a helicopter.
19. The filter system of claim 11 wherein borders of the retainer system and the frame include opposing supports for capturing the flexible border therebetween.
20. The filter system of claim 19 further comprising a seal supported by one of the supports and engaging the border for facilitating sealing around the border of the filter element.
21. The filter system of claim 20 further wherein the retainer system includes an adhesive seal between the rigid frame and the filter element.
PCT/US2007/060910 2006-01-30 2007-01-23 Engine air intake barrier filter system for aircraft WO2007090011A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US76344206P 2006-01-30 2006-01-30
US60/763,442 2006-01-30

Publications (2)

Publication Number Publication Date
WO2007090011A2 true WO2007090011A2 (en) 2007-08-09
WO2007090011A3 WO2007090011A3 (en) 2007-09-27

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1935472A1 (en) * 2006-12-18 2008-06-25 Bmc S.R.L. Vehicle engine air intake filter
EP2065305A1 (en) 2007-11-30 2009-06-03 Eurocopter Air intake for a turboshaft engine equipped with a controlled filtering system
DE102008017962A1 (en) 2008-04-08 2009-12-03 Eurocopter Deutschland Gmbh Combustion air feeding device for aircraft i.e. helicopter, engine, has air inlet pipelines extended to engines from outer surface, where air feeding of engines is switched to inlet pipelines by control device when air inlets are blocked
EP3170751A1 (en) * 2015-11-20 2017-05-24 Bell Helicopter Textron Inc. Passive internal ice protection systems for engine inlets
WO2018191147A1 (en) * 2017-04-11 2018-10-18 Cummins Filtration Ip, Inc. Panel filter element
EP3812030A1 (en) * 2019-10-23 2021-04-28 Pall Corporation Air filter and method of use
IT202100001001A1 (en) 2021-01-21 2022-07-21 Only Frank S R L ECO-SUSTAINABLE TANNING METHOD, SUITABLE FOR WASHING, TREATMENT AND PRODUCTION OF WORKABLE LEATHER AND ASSOCIATED DRUM
IT202100008651A1 (en) * 2021-04-07 2022-10-07 Bmc Srl AIR INTAKE SYSTEM PROVIDED WITH A PRE-FILTER FOR A VEHICLE ENGINE
US11992800B2 (en) 2020-11-24 2024-05-28 Cummins Filtration Inc. Arched air filter

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6228152B1 (en) * 1997-12-22 2001-05-08 Valeo Equipements Electriques Moteur Filtering device for equipping a ventilation and/or heating and/or air conditioning unit, more particularly for a motor vehicle
US20010020512A1 (en) * 2000-02-17 2001-09-13 Tanja Heilmann Reinforced, bendable filter element
WO2002013947A1 (en) * 2000-08-18 2002-02-21 Helsa-Werke Helmut Sandler Gmbh & Co. Kg Flexible filter
US20020182062A1 (en) * 2000-10-02 2002-12-05 Westar Corporation Aircraft engine air filter and method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6228152B1 (en) * 1997-12-22 2001-05-08 Valeo Equipements Electriques Moteur Filtering device for equipping a ventilation and/or heating and/or air conditioning unit, more particularly for a motor vehicle
US20010020512A1 (en) * 2000-02-17 2001-09-13 Tanja Heilmann Reinforced, bendable filter element
WO2002013947A1 (en) * 2000-08-18 2002-02-21 Helsa-Werke Helmut Sandler Gmbh & Co. Kg Flexible filter
US20020182062A1 (en) * 2000-10-02 2002-12-05 Westar Corporation Aircraft engine air filter and method

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1935472A1 (en) * 2006-12-18 2008-06-25 Bmc S.R.L. Vehicle engine air intake filter
EP2065305A1 (en) 2007-11-30 2009-06-03 Eurocopter Air intake for a turboshaft engine equipped with a controlled filtering system
DE102008017962A1 (en) 2008-04-08 2009-12-03 Eurocopter Deutschland Gmbh Combustion air feeding device for aircraft i.e. helicopter, engine, has air inlet pipelines extended to engines from outer surface, where air feeding of engines is switched to inlet pipelines by control device when air inlets are blocked
US8096499B2 (en) 2008-04-08 2012-01-17 Eurocopter Deutschland Gmbh Device for feeding combustion air to an engine of an aircraft
DE102008017962B4 (en) * 2008-04-08 2012-09-06 Eurocopter Deutschland Gmbh Apparatus for supplying combustion air to an engine of an aircraft
US10858995B2 (en) 2015-11-20 2020-12-08 Bell Helicopter Textron Inc. Passive internal ice protection systems for engine inlets
US10036320B2 (en) 2015-11-20 2018-07-31 Bell Helicopter Textron Inc. Passive internal ice protection systems for engine inlets
EP3170751A1 (en) * 2015-11-20 2017-05-24 Bell Helicopter Textron Inc. Passive internal ice protection systems for engine inlets
WO2018191147A1 (en) * 2017-04-11 2018-10-18 Cummins Filtration Ip, Inc. Panel filter element
US11369910B2 (en) 2017-04-11 2022-06-28 Cummins Filtration Ip, Inc. Panel filter element
US12053731B2 (en) 2017-04-11 2024-08-06 Cummins Filtration Ip, Inc. Panel filter element
EP3812030A1 (en) * 2019-10-23 2021-04-28 Pall Corporation Air filter and method of use
JP2021074710A (en) * 2019-10-23 2021-05-20 ポール・コーポレーションＰａｌｌ Ｃｏｒｐｏｒａｔｉｏｎ Air filter and method of use
US11596889B2 (en) 2019-10-23 2023-03-07 Pall Corporation Air filter and method of use
US11992800B2 (en) 2020-11-24 2024-05-28 Cummins Filtration Inc. Arched air filter
IT202100001001A1 (en) 2021-01-21 2022-07-21 Only Frank S R L ECO-SUSTAINABLE TANNING METHOD, SUITABLE FOR WASHING, TREATMENT AND PRODUCTION OF WORKABLE LEATHER AND ASSOCIATED DRUM
IT202100008651A1 (en) * 2021-04-07 2022-10-07 Bmc Srl AIR INTAKE SYSTEM PROVIDED WITH A PRE-FILTER FOR A VEHICLE ENGINE
DE102022001192A1 (en) 2021-04-07 2022-10-13 BMC S.r.I. AIR INTAKE SYSTEM WITH PREFILTER FOR A DRIVE OF A VEHICLE

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