CPC F02C 9/16 (2013.01) [B64D 33/02 (2013.01); F02C 7/04 (2013.01); F02C 7/06 (2013.01); F02K 3/06 (2013.01); B64D 2033/0286 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2240/50 (2013.01); F05D 2270/02 (2013.01); F05D 2270/3011 (2013.01); F05D 2270/3015 (2013.01); F05D 2270/334 (2013.01); F05D 2270/807 (2013.01)] | 20 Claims |
1. A turbine engine comprising:
a fan;
a nacelle circumscribing at least the fan;
a compressor section downstream of the fan;
a conduit defined, at least in part, by the nacelle, wherein the conduit comprises:
a first opening at the compressor section;
a second opening downstream of the fan and upstream of the compressor section; and
a third opening upstream of the fan;
a first pressure sensor located at an outer lip of the nacelle;
a second pressure sensor coupled to the nacelle and spaced from the first pressure sensor; and
at least one actuator communicatively coupled to the first pressure sensor and the second pressure sensor, the at least one actuator located in the conduit and configured to adjust airflow between the first opening and the third opening, and between the second opening and the third opening, wherein the first pressure sensor and the second pressure sensor provide outputs for generating commands that control the at least one actuator.
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