IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0080864
(2011-04-06)
|
등록번호 |
US-8387950
(2013-03-05)
|
발명자
/ 주소 |
- Hummel, Daniel Scott
- Laborie, Daniel Jean-Louis
- Holtsclaw, Bradley James
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
6 |
초록
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A flow device adapted to operate as a restrictor as well as provide a pressure relief capability in the event of an over-pressurization event within a fluid system containing the device. The flow device includes an expandable orifice that has an outer perimeter, a plurality of cantilevered tabs surr
A flow device adapted to operate as a restrictor as well as provide a pressure relief capability in the event of an over-pressurization event within a fluid system containing the device. The flow device includes an expandable orifice that has an outer perimeter, a plurality of cantilevered tabs surrounded by the outer perimeter, and an opening surrounded and defined by the tabs. The tabs project from the outer perimeter toward the opening, which restricts flow of the bleed air through the expandable orifice at a pressure below a predetermined pressure level, but then expands to relieve an over-pressure condition of the bleed air at a pressure above the predetermined pressure level as a result of the cantilevered tabs being deflected by the over-pressure condition. The device is adaptable for use in aircraft applications, including the regulation of bleed air used in anti-icing/de-icing systems.
대표청구항
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1. A flow device mounted within a passage adapted for a fluid to flow therethrough and for an anti-icing system on an aircraft engine, the flow device comprising: a panel having a thickness in a through-thickness direction thereof; and an expandable orifice defined in the panel, the expandable orifi
1. A flow device mounted within a passage adapted for a fluid to flow therethrough and for an anti-icing system on an aircraft engine, the flow device comprising: a panel having a thickness in a through-thickness direction thereof; and an expandable orifice defined in the panel, the expandable orifice comprising an outer perimeter, a plurality of cantilevered tabs surrounded by the outer perimeter and lying in a common plane, and an opening that extends through the thickness of the panel and is surrounded and defined by the cantilevered tabs, wherein each of the cantilevered tabs lies entirely in the plane and the opening has an axis parallel to the through-thickness direction of the panel, the cantilevered tabs projecting from the outer perimeter toward the opening, adjacent pairs of the cantilevered tabs being separated from each other by a gap, the gaps enabling the cantilevered tabs to deflect out of the plane thereof independently of each other, each of the cantilevered tabs defining a junction at the outer perimeter at which the cantilevered tab bends when deflected out of the plane thereof, wherein the opening is operable to restrict the fluid flowing through the expandable orifice as the fluid flows through the passage at a pressure below a predetermined pressure level, the cantilevered tabs being operable to deflect out of the plane thereof to relieve an over-pressure condition of the fluid at a pressure above the predetermined pressure level, the cantilevered tabs being entirely cantilevered within the passage so as to plastically deform at the junctions thereof while remaining cantilevered in response to the pressure within the passage being above the predetermined pressure level. 2. The flow device according to claim 1, wherein the cantilevered tabs project radially inward from the outer perimeter toward a central axis of the opening. 3. The flow device according to claim 1, wherein the gaps between the adjacent pairs of the cantilevered tabs are located on radials of an axis of the opening. 4. The flow device according to claim 1, wherein the outer perimeter of the expandable orifice has a circular shape, and the junction of each of the cantilevered tabs with the outer perimeter has an arcuate shape coinciding with the circular shape of the outer perimeter. 5. The flow device according to claim 1, further comprising peripheral gaps disposed in the outer perimeter of the expandable orifice, each of the peripheral gaps being contiguous with one of the gaps between the adjacent pairs of the cantilevered tabs, and each of the junctions of the cantilevered tabs is between adjacent pairs of the peripheral gaps. 6. The flow device according to claim 1, wherein the through-thickness of the panel is up to about 4 mm. 7. The flow device according to claim 1, wherein the panel is formed of a metallic material. 8. The flow device according to claim 1, wherein the flow device is a component of an anti-icing system installed on an aircraft engine, and the duct discharges bleed air drawn from a compressor of the aircraft engine to heat a fan cowling of the aircraft engine. 9. The anti-icing system according to claim 8. 10. An anti-icing system installed on an aircraft engine, the anti-icing system comprising: a duct fluidically coupled to a compressor of the aircraft engine and adapted to draw bleed air from the compressor;a cavity within a fan cowling of the aircraft engine, the cavity being fluidically coupled to the duct to receive the bleed air from the duct; anda flow device fluidically coupled to the duct for discharging the bleed air into the cavity, the flow device comprising an expandable orifice having an outer perimeter, a plurality of cantilevered tabs surrounded by the outer perimeter and each entirely lying in a common plane, and an opening surrounded and defined by the cantilevered tabs, the cantilevered tabs projecting from the outer perimeter toward the opening, adjacent pairs of the cantilevered tabs being separated from each other by a gap, the gaps enabling the cantilevered tabs to deflect out of the plane thereof independently of each other, each of the cantilevered tabs defining a junction at the outer perimeter at which the cantilevered tab bends when deflected out of the plane thereof, wherein the opening is operable to restrict the bleed air flowing through the expandable orifice as the bleed air flows through the duct at a pressure below a predetermined pressure level, the cantilevered tabs being operable to deflect out of the plane thereof to relieve an over-pressure condition of the bleed air at a pressure above the predetermined pressure level, the cantilevered tabs being entirely cantilevered within the duct so as to plastically deform at the junctions thereof while remaining cantilevered in response to the pressure within the duct being above the predetermined pressure level. 11. The anti-icing system according to claim 10, wherein the cantilevered tabs project radially inward from the outer perimeter toward a central axis of the opening. 12. The anti-icing system according to claim 10, wherein the gaps between the adjacent pairs of the cantilevered tabs are located on radials of an axis of the opening. 13. The anti-icing system according to claim 10, wherein the outer perimeter of the expandable orifice has a circular shape, and the junction of each of the cantilevered tabs with the outer perimeter has an arcuate shape coinciding with the circular shape of the outer perimeter. 14. The anti-icing system according to claim 10, further comprising peripheral gaps disposed in the outer perimeter of the expandable orifice, each of the peripheral gaps being contiguous with one of the gaps between the adjacent pairs of the cantilevered tabs, and each of the junctions of the cantilevered tabs is between adjacent pairs of the peripheral gaps. 15. A method of inhibiting ice build-up on a fan cowling of an aircraft engine, the method comprising: operating the aircraft engine;drawing bleed air from a compressor of the aircraft engine; and introducing the bleed air into the fan cowling through a flow device, the flow device comprising an expandable orifice having an outer perimeter, a plurality of cantilevered tabs surrounded by the outer perimeter, and an opening surrounded and defined by the cantilevered tabs, the cantilevered tabs projecting from the outer perimeter toward the opening, wherein each of the cantilevered tabs lies entirely in a common plane and deflect out of the plane to relieve the over-pressure condition;wherein the opening restricts flow of the bleed air through the expandable orifice at a pressure below a predetermined pressure level; andwherein the cantilevered tabs plastically deform while remaining cantilevered to cause the opening to permanently expand to relieve an over-pressure condition of the bleed air at a pressure above the predetermined pressure level as a result of the cantilevered tabs being deflected by the over-pressure condition. 16. The method according to claim 15, wherein adjacent pairs of the cantilevered tabs deflect independently of each other. 17. The method according to claim 15, wherein each of the cantilevered tabs define a junction at the outer perimeter at which the cantilevered tabs bend and plastically deform when deflected by the over-pressure condition. 18. The method according to claim 15, wherein the expandable orifice further comprises gaps between adjacent pairs of the cantilevered tabs that enable the adjacent pairs to deflect independently of each other.
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