Gas turbine engine
A gas turbine engine includes an unducted primary fan, a core engine including a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding the core engine. The core cowl has a cowl door. The outer surface of the core cowl defines a peak cowl diameter (D), and the outer surface of the combustor casing defines a maximum combustor casing diameter (d). The core engine defines an overall core axial length (L) and an under-core cowl axial length (L 1 ). The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L 1 ) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.
1 . A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a turbomachine having an unducted primary fan, a core engine including a combustor and a combustor casing enclosing the combustor and defining an outer surface, the core engine defining a first stream axially through the core engine;
a fan cowl that circumferentially surrounds at least a portion of the core engine and having an exterior surface defining a second stream along the exterior surface and a fan duct located between the exterior surface and the core engine and defining a third stream; and
a core cowl having an outer surface and an inner surface and including a cowl door located in the fan cowl that is movable between an opened position and a closed position to provide selective access to at least a portion of the core engine, the cowl door defining at least a portion of the fan duct,
wherein the outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction, the core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L 1 ) along the axial direction,
wherein the gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L 1 ) divided by the overall core axial length (L),
wherein the CDR is between 2.7 and 3.5 and wherein the CLR is between 0.25 and 0.50.
2 . The gas turbine engine of claim 1 , wherein the cowl door comprises an inner cowling and an outer cowling located radially outward from the inner cowling with respect to the core engine, a space between the inner cowling and the outer cowling defining at least a portion of the fan duct.
3 . The gas turbine engine of claim 1 , wherein the cowl door extends across 180 degrees of the core engine.
4 . The gas turbine engine of claim 1 , wherein the fan duct forms an annulus about the core engine.
5 . The gas turbine engine of claim 4 , wherein the annulus is discontinuous.
6 . The gas turbine engine of claim 5 , wherein the annulus extends, in total, at least 240 degrees about the core engine.
7 . The gas turbine engine of claim 1 , wherein the fan cowl comprises a hinge mounting the cowl door to the fan cowl.
8 . The gas turbine engine of claim 7 , wherein the fan cowl further comprises an engine mount and the hinge is located adjacent the engine mount.
9 . The gas turbine engine of claim 8 , wherein the cowl door comprises a plurality of cowl doors, with the fan cowl having a hinge for each of the plurality of cowl doors, with each hinge located at the engine mount.
10 . The gas turbine engine of claim 9 , wherein each of the plurality of cowl doors includes an inner cowling, an outer cowling, and a hinge edge coupled to a corresponding hinge such that at least one of the inner cowling or the outer cowling of each of the plurality of cowl doors is moveable between the opened position and the closed position.
11 . An aircraft comprising:
a wing; and
a gas turbine engine mounted to the wing, the gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a turbomachine having an unducted primary fan, a core engine including a combustor and a combustor casing enclosing the combustor and defining an outer surface, the core engine defining a first stream axially through the core engine;
a fan cowl that circumferentially surrounds at least a portion of the core engine and having an exterior surface defining a second stream along the exterior surface and a fan duct located between the exterior surface and the core engine and defining a third stream; and
a core cowl having an outer surface and an inner surface and including a cowl door located in the fan cowl that is movable between an opened position and a closed position to provide selective access to at least a portion of the core engine, the cowl door defining at least a portion of the fan duct;
wherein the outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction, the core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L 1 ) along the axial direction,
wherein the gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L 1 ) divided by the overall core axial length (L), and
wherein the CDR is between 2.7 and 3.5 and wherein the CLR is between 0.25 and 0.50.
12 . The aircraft of claim 11 , wherein the cowl door comprises an inner cowling and an outer cowling located radially outward from the inner cowling with respect to the core engine, a space between the inner cowling and the outer cowling defining at least a portion of the fan duct.
13 . The aircraft of claim 11 , wherein the cowl door extends across 180 degrees of the core engine.
14 . The aircraft of claim 11 , wherein the fan duct forms an annulus about the core engine.
15 . The aircraft of claim 14 , wherein the annulus is discontinuous.
16 . The aircraft of claim 15 , wherein the annulus extends, in total, at least 240 degrees about the core engine.
17 . The aircraft of claim 11 , wherein the fan cowl comprises a hinge mounting the cowl door to the fan cowl.
18 . The aircraft of claim 17 , wherein the fan cowl further comprises an engine mount and the hinge is located adjacent the engine mount.
19 . The aircraft of claim 18 , wherein the cowl door comprises a plurality of cowl doors, with the fan cowl having a hinge for each of the plurality of cowl doors, with each hinge located at the engine mount.
20 . The aircraft of claim 19 , wherein each of the plurality of cowl doors includes an inner cowling, an outer cowling, and a hinge edge coupled to the corresponding hinge such that at least one of the inner cowling or the outer cowling of each of the plurality of cowl doors is moveable between the opened position and the closed position.