Arrangements and methods for supplying heated air to a wing anti-icing system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-015/04
B64D-013/08
B64D-013/06
출원번호
US-0084209
(2016-03-29)
등록번호
US-10239626
(2019-03-26)
발명자
/ 주소
Herchenroder, Anthony
Paul, Douglas
Landers, Stephen
출원인 / 주소
Gulfstream Aerospace Corporation
대리인 / 주소
LKGlobal | Lorenz & Kopf, LLP
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
An arrangement for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine includes, but is not limited to, an ejector that is configured for coupling to a wing anti-icing system. The ejector is further configured to receive a first flow of air, to entrain a second
An arrangement for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine includes, but is not limited to, an ejector that is configured for coupling to a wing anti-icing system. The ejector is further configured to receive a first flow of air, to entrain a second flow of air with the first flow of air, the second flow of air having a lower temperature than the first flow of air, to mix the first flow of air with the second flow of air to form a combined flow having a temperature and a volume suitable for use by the wing anti-icing system, and to exhaust the combined flow into the wing anti-icing system.
대표청구항▼
1. An arrangement for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine, the arrangement comprising: a pre-cooler configured to receive a flow of bleed-air from the jet engine, to receive a flow of cooling-air from a freestream, to cool the flow of bleed-air w
1. An arrangement for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine, the arrangement comprising: a pre-cooler configured to receive a flow of bleed-air from the jet engine, to receive a flow of cooling-air from a freestream, to cool the flow of bleed-air with the flow of cooling-air, to exhaust a flow of cooled bleed air, and to exhaust a flow of warmed cooling-air; andan ejector configured to:receive a portion of the flow of cooled bleed-air from the pre-cooler,to entrain a portion of the flow of warmed cooling-air with the portion of the flow of cooled bleed-air,to mix the portion of the flow of cooled bleed-air with the portion of the flow of warmed cooling-air to form a combined flow having a temperature and a volume suitable for use by the wing anti-icing system, andto exhaust the combined flow. 2. The arrangement of claim 1, wherein the ejector is configured to accommodate the flow of cooled bleed-air having a temperature range of two hundred to three hundred degrees Fahrenheit (93.3 to 148.9 degrees Celcius). 3. The arrangement of claim 2, wherein the ejector is configured to accommodate the flow of cooled bleed-air having a temperature of two hundred fifty degrees Fahrenheit (121.1 degrees Celcius). 4. The arrangement of claim 1, wherein the ejector is configured to accommodate the flow of warmed cooling-air at a temperature range of eighty degrees to one hundred degrees Fahrenheit (26.7 to 37.8 degrees Celcius). 5. The arrangement of claim 4, wherein the ejector is configured to accommodate the flow of warmed cooling-air at a temperature of ninety degrees Fahrenheit (32.2 degrees Celcius). 6. The arrangement of claim 1, wherein the ejector is configured to mix the portion of the flow of cooled bleed-air and the portion of the flow of warmed cooling-air until the combined flow has a temperature range of one hundred twenty degrees to one hundred eighty degrees Fahrenheit (48.9 to 82.2 degrees Celcius). 7. The arrangement of claim 6, wherein the ejector is configured to mix the portion of the flow of cooled bleed-air and the portion of the flow of warmed cooling-air until the combined flow has a temperature of one hundred sixty degrees Fahrenheit (71.1 degrees Celcius). 8. The arrangement of claim 1, wherein the ejector is configured to yield the combined flow having a ratio of warmed cooling-air to cooled bleed-air of ten to one. 9. The arrangement of claim 1, wherein the ejector is configured to yield the combined flow having a ratio of warmed cooling-air to cooled bleed-air of one hundred to one. 10. The arrangement of claim 1, wherein the ejector is configured to entrain all of the flow of warmed cooling-air with the portion of the flow of cooled bleed-air. 11. A method for supplying heated air to a wing anti-icing system on an aircraft propelled by a jet engine, the method comprising the steps of: receiving a flow of bleed-air from the jet engine and a flow of cooling-air from a freestream at a pre-cooler;cooling the flow of bleed-air with the flow of cooling-air at the pre-cooler;exhausting a flow of cooled bleed-air and a flow of warmed cooling-air from the pre-cooler;receiving a portion of the flow of cooled bleed-air at an ejector;entraining a portion of the flow of warmed cooling-air with the portion of the flow of cooled bleed-air at the ejector;mixing the portion of the flow of warmed cooling-air with the portion of the flow of cooled-bleed air at the ejector to form a combined flow; andexhausting the combined flow from the ejector. 12. The method of claim 11, further comprising the step of directing the combined flow to the wing anti-icing system. 13. The method of claim 12, further comprising the step of de-icing a wing of the aircraft with the combined flow. 14. The method of claim 11, wherein the mixing step comprises mixing the portion of the flow of warmed cooling-air and the portion of the flow of cooled-bleed air to a ratio of ten to one. 15. The method of claim 11, wherein the mixing step comprises mixing the portion of the flow of warmed cooling-air and the portion of the flow of cooled-bleed air to a ratio of one hundred to one. 16. The method of claim 11, wherein the mixing step comprises mixing the portion of the flow of warmed cooling-air and the portion of the flow of cooled bleed-air until the combined flow has a temperature range of one hundred twenty degrees to one hundred eighty degrees Fahrenheit (48.9 to 82.2 degrees Celcius). 17. The method of claim 16, wherein the mixing step comprises mixing the portion of the flow of warmed cooling-air and the portion of the flow of cooled bleed-air until the combined flow has a temperature of one hundred sixty degrees Fahrenheit (71.1 degrees Celcius). 18. The method of claim 11, wherein the step of entraining the portion of the flow of warmed cooling-air with the portion of the flow of cooled bleed-air at the ejector comprises entraining all of the flow of warmed cooling-air.
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