Aeroengine thrust reverser
A gas turbine engine comprising a core engine a fan and a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes characterised in that a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support.
1. A gas turbine engine comprising:
a core engine;
a fan; and
a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes, wherein a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support, and wherein the second support is a frame having an A shape.
2. A gas turbine engine as claimed in claim 1 wherein each frame comprises an apex attached to the cascade and two ends attached to the core casing.
3. A gas turbine engine as claimed in claim 1 wherein each frame is attached to the core casing adjacent an array of vanes.
4. A gas turbine engine as claimed in claim 1 wherein the second support is an array of spokes.
5. A gas turbine engine as claimed in claim 1 wherein the cascade is annular and capable of carrying hoop stress.
6. A gas turbine engine as claimed in claim 1 wherein the rigid attachment is by virtue of the fan casing and cascade being a unitary structure.
7. A gas turbine engine as claimed in claim 1 wherein the cascade is rigidly attached to the fan casing by any one of the group comprising a bolted or a welded joint.
8. A gas turbine engine as claimed in claim 1 wherein the cascade is rigidly attached to the fan casing via a ramp fairing.
9. A gas turbine engine as claimed in claim 1 wherein the cascade is positioned between inner and outer translatable cowls in a stowed position and is exposed to an airflow B when the translatable cowls are in a deployed position.
10. A gas turbine engine as claimed in claim 9 wherein the cascade is positioned in a radially outward part of a space between inner and outer cowls.
11. A gas turbine engine as claimed in claim 9 wherein the cascade extends substantially from adjacent the inner cowl to adjacent the outer cowl.
12. A gas turbine engine comprising:
a core engine;
a fan; and
a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes, wherein a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support, and wherein the second support comprises at least two frames having an A shape, one positioned at each of the top and bottom of the engine.
13. A gas turbine engine comprising:
a core engine;
a fan; and
a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes, wherein a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support, and wherein the second support is an array of spokes, and wherein the spokes are vanes.
14. A gas turbine engine comprising:
a core engine;
a fan; and
a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes, wherein a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support, and wherein the cascade is further rigidly attached to the fan casing via a torque box.
15. A gas turbine engine comprising:
a core engine;
a fan; and
a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes, wherein a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support, and wherein the core casing is surrounded by a core fairing and engine accessories are mounted between the core casing and the core fairing.