Multipiece nose cone for open rotor propulsion system
A propulsion system assembly includes an open propulsor rotor, an open guide vane structure and a nose cone. The open propulsor rotor is configured to rotate about an axis. The open guide vane structure is aft of the open propulsor rotor along the axis. The nose cone is forward of the open propulsor rotor along the axis. The nose cone includes a forward tip end, an aft base end, a stationary section and a rotating section. The aft base end is adjacent to the open propulsor rotor. The stationary section projects axially along the axis from a junction between the stationary section and the rotating section to the forward tip end. The rotating section projects axially along the axis from the junction between the stationary section and the rotating section to the aft base end. The rotating section is configured to rotate with the open propulsor rotor about the axis.
1 . An assembly for an aircraft propulsion system, comprising:
an open propulsor rotor configured to rotate about an axis;
an open guide vane structure aft of the open propulsor rotor along the axis; and
a nose cone forward of the open propulsor rotor along the axis, the nose cone including a forward tip end, an aft base end, a stationary section and a rotating section, the aft base end adjacent to the open propulsor rotor, the stationary section projecting axially along the axis from a junction between the stationary section and the rotating section to the forward tip end, the rotating section projecting axially along the axis from the junction between the stationary section and the rotating section to the aft base end, and the rotating section configured to rotate with the open propulsor rotor about the axis.
2 . The assembly of claim 1 , wherein
the nose cone has an axial length extending between the forward tip end and the aft base end; and
an axial distance from the forward tip end to the junction between the stationary section and the rotating section is equal to or greater than fifty percent of the axial length.
3 . The assembly of claim 1 , wherein
the nose cone has an axial length extending between the forward tip end and the aft base end; and
an axial distance from the forward tip end to the junction between the stationary section and the rotating section is equal to or less than eighty percent of the axial length.
4 . The assembly of claim 1 , wherein a sidewall of the stationary section is flush with a sidewall of the rotating section at the junction between the stationary section and the rotating section.
5 . The assembly of claim 1 , wherein a sidewall of the rotating section is radially outboard of and axially overlaps a sidewall of the stationary section at the junction between the stationary section and the rotating section.
6 . The assembly of claim 1 , wherein a sidewall of the stationary section is radially outboard of a sidewall of the rotating section at the junction between the stationary section and the rotating section.
7 . The assembly of claim 1 , wherein an overlap between a sidewall of the stationary section and a sidewall of the rotating section at the junction between the stationary section and the rotating section is symmetrical about the axis.
8 . The assembly of claim 1 , wherein an overlap between a sidewall of the stationary section and a sidewall of the rotating section at the junction between the stationary section and the rotating section is asymmetrical about the axis.
9 . The assembly of claim 1 , wherein
the nose cone further includes an air scoop disposed at the junction between the stationary section and the rotating section; and
the air scoop is configured to direct air into an internal volume of the nose cone.
10 . The assembly of claim 9 , wherein the air scoop is formed by the stationary section and the rotating section.
11 . The assembly of claim 1 , further comprising:
an air passage internal to the aircraft propulsion system;
the stationary section and the rotating section forming an air scoop at the junction between the stationary section and the rotating section, and the air scoop configured to fluidly couple an environment external to the nose cone with the air passage.
12 . The assembly of claim 1 , wherein the nose cone further includes an air scoop disposed at the junction between the stationary section and the rotating section, and the assembly further comprises:
an air system fluidly coupled to the air scoop;
the air system configured to use air received from the air scoop to cool one or more internal components of the aircraft propulsion system.
13 . The assembly of claim 1 , wherein the nose cone further includes an air scoop disposed at the junction between the stationary section and the rotating section, and the assembly further comprises:
an air system fluidly coupled to the air scoop;
the air system configured to use air received from the air scoop to vent one or more internal volumes within the aircraft propulsion system.
14 . The assembly of claim 1 , wherein
the open propulsor rotor includes a platform and a plurality of open propulsor blades projecting radially out from the platform; and
the rotating section is discrete from the platform.
15 . The assembly of claim 1 , wherein the rotating section is mechanically fastened to the open propulsor rotor.
16 . The assembly of claim 1 , further comprising a turbine engine configured to drive rotation of the open propulsor rotor and the rotating section about the axis.
17 . An assembly for an aircraft propulsion system, comprising:
an open propulsor rotor configured to rotate about an axis; and
a nose cone upstream of the open propulsor rotor, the nose cone including a forward tip end, an aft base end, a stationary section, a rotating section and an air scoop, the aft base end bordering the open propulsor rotor, the stationary section projecting axially along the axis from a junction between the stationary section and the rotating section to the forward tip end, the rotating section projecting axially along the axis from the junction between the stationary section and the rotating section to the aft base end, the rotating section configured to rotate with the open propulsor rotor about the axis, and the air scoop located at the junction between the stationary section and the rotating section.
18 . The assembly of claim 17 , wherein
the nose cone has an axial length extending between the forward tip end and the aft base end; and
an axial distance from the forward tip end to the junction between the stationary section and the rotating section is between fifty percent and eighty percent of the axial length.
19 . The assembly of claim 17 , further comprising an air system configured to receive air from outside of the aircraft propulsion system through the air scoop.
20 . An assembly for an aircraft propulsion system, comprising:
an open propulsor rotor configured to rotate about an axis; and
a nose cone upstream of the open propulsor rotor, the nose cone including a forward tip end, an aft base end, a stationary section and a rotating section, the aft base end bordering the open propulsor rotor, the stationary section projecting axially along the axis from a junction between the stationary section and the rotating section to the forward tip end, the rotating section projecting axially along the axis from the junction between the stationary section and the rotating section to the aft base end, and the rotating section configured to rotate with the open propulsor rotor about the axis;
wherein a sidewall of the stationary section axially overlaps a sidewall of the rotating section at the junction between the stationary section and the rotating section.