Back to results
US 9,038,367 B2Granted
Fan case thrust reverser
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Brian D. Merry, Allan R. Penda, Christopher M. Dye, Jay Bhatt
Life of this patent
Estimating the term…
Abstract
A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.
Claims20
A fan case of a gas turbine engine comprising:
- a fan blade containment section defined about anengine axis;
- a thrust reverser cascade section downstream of said blade containment section, said thrust reverser cascade section including an array of cascade airfoils and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix;
- and
- a Fan Exit Guide Vane section downstream of said thrust reverser cascade section.
1 more element
A fan section of a gas turbine engine comprising:
- a fan case defined about an engine axis;
- a multiple of Fan Exit Guide Vanes attached to said fan case;
- and
- a thrust reverser cascade section upstream of said multiple of Fan Exit Guide Vanes, said thrust reverser cascade section including an array of cascade airfoils arranged among a plurality of ribs that are in a helix arrangement and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix.
1 more element
A gas turbine engine comprising:
- a fan case defined about an engine axis;
- a core case defined about said engine axis;
- a multiple of Fan Exit Guide Vanes attached to said fan case and said core case;
- a thrust reverser cascade section upstream of said multiple of Fan Exit Guide Vanes, said thrust reverser cascade section including an array of cascade airfoils, a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix, and said array of cascade airfoils being arranged among a plurality of ribs that are in a helix arrangement.
1 more element
Dependencies are inferred from the claim text.