Gas turbine engine mounting arrangement
AssigneeROLLS-ROYCE plc
InventorsRichard G. STRETTON, Steven A. RADOMSKI
Life of this patent
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Abstract
A gas turbine engine (10) comprises a bypass duct cowl (21), an engine core housing (22) defining an engine core inlet, a bypass fan (13) and a plurality of outlet guide vanes (24). Each outlet guide vane 24 extends between a radially inner surface of the bypass duct cowl (21) and a radially outer surface of the engine core housing (22, 23) to define an outlet guide vane span (SPANOGV). The outlet guide vanes (24) are configured to support the engine core housing (22, 23) relative to the bypass duct cowl (21). The bypass fan (13) and an engine core inlet (34) define a bypass ratio between 10 and 17, and a ratio of the outlet guide vane span (OGVSPAN) to a bypass fan radius (RFAN) is between 0.45 and 0.55.
Claims7
A gas turbine engine comprising:
- a bypass duct cowl;
- an engine core housing defining an engine core inlet;
- a bypass fan;
- and
- a plurality of outlet guide vanes extending between a radially inner surface of the bypass duct cowl, and a radially outer surface of the engine core housing to define an outlet guide vane span, the outlet guide vanes being configured to support the engine core housing relative to the bypass duct cowl;
- wherein the bypass fan and an engine core inlet define a bypass ratio between 10 and 17;
- and a ratio of the outlet guide vane span to a bypass fan radius is between 0.45 and 0.55.
Dependencies are inferred from the claim text.