Arrangements and methods for supplying heated air to a wing anti-icing system
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.
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; and
an 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, and
to 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; and
exhausting 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.