US 12,275,532 B2
Gas turbine engine noise reduction
Kishore Ramakrishnan, Rexford, NY (US); Trevor Howard Wood, Clifton Park, NY (US); Harry Kirk Mathews, Jr., Clifton Park, NY (US); Eric Richard Westervelt, Niskayuna, NY (US); Honggang Wang, Clifton Park, NY (US); and Timothy Richard DePuy, Liberty Township, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Aug. 15, 2022, as Appl. No. 17/887,872.
Prior Publication US 2024/0051673 A1, Feb. 15, 2024
Int. Cl. B64D 31/06 (2024.01); B64D 27/10 (2006.01); B64D 27/24 (2024.01); B64D 27/02 (2006.01)
CPC B64D 31/06 (2013.01) [B64D 27/10 (2013.01); B64D 27/24 (2013.01); B64D 27/026 (2024.01); F05D 2270/333 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft engine comprising:
a low pressure spool;
a high pressure spool;
a primary power source configured to provide first power to the engine;
an alternative power source configured to add second power to the high pressure spool, wherein the second power is in addition to the first power provided to the engine by the primary power source, wherein the engine is configured to produce an overall level of thrust; and
a controller configured to:
determine a noise sensitive condition based on at least one of a location along a flight path or an altitude above ground level; and
control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool, and
reduce, in response to determining the noise sensitive condition, a speed of the low pressure spool while maintaining the overall level of thrust.