US 12,006,891 B2
Propulsor wing trailing edge exhaust area control
Mark Douglass Moore, Crossville, TN (US); Ian Andreas Villa, Crossville, TN (US); and Devon Jedamski, Crossville, TN (US)
Assigned to Whisper Aero Inc., Crossville, TN (US)
Filed by Whisper Aero Inc., Crossville, TN (US)
Filed on Feb. 24, 2022, as Appl. No. 17/679,540.
Claims priority of provisional application 63/156,067, filed on Mar. 3, 2021.
Claims priority of provisional application 63/156,063, filed on Mar. 3, 2021.
Claims priority of provisional application 63/156,073, filed on Mar. 3, 2021.
Claims priority of provisional application 63/156,076, filed on Mar. 3, 2021.
Prior Publication US 2022/0349361 A1, Nov. 3, 2022
Int. Cl. B64D 33/04 (2006.01); F02K 1/08 (2006.01); F02K 1/12 (2006.01)
CPC F02K 1/1207 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/128 (2013.01); F05D 2250/12 (2013.01); F05D 2250/141 (2013.01); F05D 2260/57 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An exhaust control system comprising:
a tail cone configured to be directly connected to a stator of a propulsor fan, the tail cone including:
a first end of the tail cone having a plurality of concentric rings including a first ring and a second ring, the first ring including a first end that is configured to connect to the stator of the propulsor fan and a second end that is opposite the first end of the first ring, and the second ring including a first end that overlaps the second end of the first ring such that the second end of the first ring is inserted into the first end of the second ring and a second end of the second ring;
a second end of the tail cone that is opposite the first end; and
an intermediate portion having an end and the second end of the second ring is inserted into the end of the intermediate portion, and the intermediate portion is disposed between the second end of the second ring and the second end of the tail cone, the intermediate portion having a diameter that is greater than a diameter of the first end of the tail cone and a diameter of the second end of the tail cone; and
an exhaust area control mechanism configured to adjust an amount of overlap between the second end of the first ring and the first end of the second ring of the tail cone and adjust an amount of overlap between the second end of the second ring and the intermediate portion of the tail cone to adjust a length of the tail cone such that a position of the intermediate portion within an outlet of the propulsor fan changes thereby varying an area of the outlet of the propulsor fan.