Gas turbine engine
A gas turbine engine includes an unducted primary fan and an engine core having a combustor casing that defines an outer surface. A core cowl surrounds the core engine where an accessory gearbox is at least partially located within the core cowl. In a radial direction, an 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). A core cowl diameter ratio (CDR) is the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and is between 2.7 and 3.5. In an axial direction, the core engine defines an overall core axial length (L) and an under-core cowl axial length (L1). A core cowl length ratio (CLR) is the under-core cowl axial length (L1) divided by the overall core axial length (L) and 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, a core cowl surrounding at least a portion of the core engine and defining an inner surface and an outer surface; and
an accessory gearbox, wherein at least a portion of the accessory gearbox is located between the core cowl and the core engine,
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 (L1) 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 (L1) 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 , further comprising at least one strut that couples the core cowl to a fan cowl, wherein the strut includes a hollow portion.
3 . The gas turbine engine of claim 2 , wherein the accessory gearbox includes a first portion located between the core cowl and the core engine, and a second portion, extending from the first portion, located in the hollow portion of the strut.
4 . The gas turbine engine of claim 3 , wherein the second portion defines a base from which a first arm and a second arm of the first portion extend to define a Y-shaped object.
5 . The gas turbine engine of claim 3 , wherein the first portion includes a single arm.
6 . The gas turbine engine of claim 3 , further comprising a first accessory device located between the core cowl and the core engine.
7 . The gas turbine engine of claim 6 , further comprising a second accessory device located in the hollow portion of the strut and operably coupled to the second portion of the accessory gearbox.
8 . The gas turbine engine of claim 3 , wherein the accessory gearbox is a first accessory gearbox, and the gas turbine engine further comprising a second accessory gearbox located in the fan cowl and operably coupled to the first accessory gearbox.
9 . The gas turbine engine of claim 8 , further comprising a third accessory device operably coupled to the second accessory gearbox and located in the fan cowl.
10 . The gas turbine engine of claim 3 , wherein the accessory gearbox is located between the core cowl and the outer surface of the combustor casing.
11 . The gas turbine engine of claim 1 , wherein the CDR is between 2.8 and 3.3.
12 . The gas turbine engine as in claim 1 , wherein the CLR is between 0.3 and 0.45.
13 . The gas turbine engine as in claim 1 , further comprising a ducted secondary fan disposed downstream from a primary fan.
14 . The gas turbine engine as in claim 13 , wherein the gas turbine engine is a three-stream gas turbine engine.
15 . 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, a core cowl surrounding at least a portion of the core engine and defining an inner surface and an outer surface; and
an accessory gearbox, wherein at least a portion of the accessory gearbox is located between the core cowl and the core engine,
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 (L1) 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 (L1) 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.
16 . The aircraft as in claim 15 , wherein a void is defined between the outer surface of the combustor casing and the inner surface of the core cowl of the gas turbine engine.
17 . The aircraft of claim 16 , further comprising a first accessory device operably coupled to the accessory gearbox and located in the void.
18 . The aircraft of claim 16 , further comprising at least one strut that couples the core cowl to a fan cowl, wherein the strut includes a hollow portion.
19 . The aircraft of claim 18 , wherein the accessory gearbox includes a first portion located in the void, and a second portion, extending from the first portion, at least partially located in the hollow portion of the strut.
20 . The aircraft of claim 19 , further comprising an accessory device at least partially located in the hollow portion of the strut and operably coupled to the accessory gearbox.