Back to results
US 10,472,081 B2Granted
Cross flow fan for wide aircraft fuselage
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Jesse M. Chandler, Wesley K. Lord
Life of this patent
Estimating the term…
Abstract
A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.
Claims21
A cross flow fan and gas turbine engine arrangement to be incorporated into an aircraft fuselage comprising:
- the cross flow fan having an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface;
- a drive arrangement for said ingestion fan rotor;
- and
- main gas turbine engines to be mounted remotely from said ingestion fan rotor, and a combined propulsion provided by said ingestion fan and rotor and said main gas turbine engines being defined in combination, and said ingestion fan rotor providing greater than or equal to 10 percent and less than or equal to 25 percent of the combined propulsion.
1 more element
An aircraft comprising:
- an aircraft fuselage having a relatively wide cross-sectional area at a location forward of a tail;
- main gas turbine engines for driving the aircraft mounted at a location remote from said relatively wide portion of said fuselage;
- a cross flow fan having an ingestion fan rotor positioned at said wide cross-sectional area to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface;
- a drive arrangement for said ingestion fan rotor;
- and
- wherein there is a combined propulsion provided by said ingestion fan rotor and said main gas turbine engines in combination, and said ingestion fan rotor providing greater than or equal to about 10% and less than or equal to about 25% of the total propulsion.
3 more elements
Dependencies are inferred from the claim text.