Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

  • US 9,920,653 B2
  • Filed: 12/20/2012
  • Issued: 03/20/2018
  • Est. Priority Date: 12/20/2012
  • Status: Active Grant
First Claim
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1. A gas turbine engine assembly, comprising:

  • a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, the fan being configured to deliver a portion of air into a compressor section and a portion of air into a bypass duct, wherein a bypass ratio is greater than 6, the bypass ratio being a ratio of a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section; and

    an inlet portion forward of the fan, a length of the inlet portion having a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion,wherein a dimensional relationship of L/D is between 0.2 and 0.45.

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