Aircraft with symmetric propulsion system rotating patterns
A first core turbine rotor of a first propulsion system is disposed in a first core turbine section and is configured to rotate in a first rotational direction. A first power turbine rotor is disposed in a first power turbine section and is configured to rotate in the first rotational direction. The first power turbine rotor is operatively coupled to a first open propulsor rotor. A second core turbine rotor of a second propulsion system is disposed in a second core turbine section and is configured to rotate in the first rotational direction. A second power turbine rotor is disposed in a second power turbine section and is configured to rotate in a second rotational direction that is opposite the first rotational direction. The second power turbine rotor is operatively coupled to a second open propulsor rotor.
1 . An aircraft system, comprising:
a first propulsion system including a first open propulsor rotor rotatable around a first axis, a first core compressor section, a first core combustor section, a first core turbine section, a first power turbine section, a first flowpath, a first core turbine rotor, a first power turbine rotor, and a first open guide vane structure, the first flowpath extending through the first core compressor section, the first core combustor section, the first core turbine section and the first power turbine section from an inlet into the first flowpath to an exhaust from the first flowpath, the first core turbine rotor disposed in the first core turbine section and configured to rotate in a first rotational direction, the first power turbine rotor disposed in the first power turbine section and configured to rotate in the first rotational direction, and the first power turbine rotor operatively coupled to the first open propulsor rotor, and the first open guide vane structure axially next to and downstream of the first open propulsor rotor,
wherein the first open guide vane structure is selectively rotationally fixed or rotatable about the first axis; and
a second propulsion system including a second open propulsor rotor rotatable around a second axis, a second core compressor section, a second core combustor section, a second core turbine section, a second power turbine section, a second flowpath, a second core turbine rotor, a second power turbine rotor and a second open guide vane structure, the second flowpath extending through the second core compressor section, the second core combustor section, the second core turbine section and the second power turbine section from an inlet into the second flowpath to an exhaust from the second flowpath, the second core turbine rotor disposed in the second core turbine section and configured to rotate in the first rotational direction, the second power turbine rotor disposed in the second power turbine section and configured to rotate in a second rotational direction that is opposite the first rotational direction, and the second power turbine rotor operatively coupled to the second open propulsor rotor, and the second open guide vane structure axially next to and downstream of the second open propulsor rotor,
wherein the second open guide vane structure is selectively rotationally fixed or rotatable about the second axis.
2 . The aircraft system of claim 1 , wherein the first open propulsor rotor is configured to rotate in an opposite rotational direction than the second open propulsor rotor.
3 . The aircraft system of claim 1 , wherein
the first open propulsor rotor is configured to rotate in the first rotational direction; and
the second open propulsor rotor is configured to rotate in the second rotational direction.
4 . The aircraft system of claim 1 , wherein
the first open propulsor rotor is configured to rotate in the second rotational direction; and
the second open propulsor rotor is configured to rotate in the first rotational direction.
5 . The aircraft system of claim 1 , wherein at least one of the first propulsion system further includes a first module and a first engine core, the first module includes the first open propulsor rotor and the first open guide vane structure, the first engine core includes the first core compressor section, the first core combustor section and the first core turbine section, and the first module is configured to be installed with or removed from the first engine core as a complete unit; or the second propulsion system further includes a second module and a second engine core, the second module includes the second open propulsor rotor and the second open guide vane structure, the second engine core includes the second core compressor section, the second core combustor section and the second core turbine section, and the second module is configured to be installed with or removed from the second engine core as a complete unit.
6 . The aircraft system of claim 1 , wherein at least one of
the first propulsion system further includes a first module and a first engine core, the first module includes the first open propulsor rotor and the first power turbine section, the first engine core includes the first core compressor section, the first core combustor section and the first core turbine section, and the first module is configured to be installed with or removed from the first engine core as a complete unit; or
the second propulsion system further includes a second module and a second engine core, the second module includes the second open propulsor rotor and the second power turbine section, the second engine core includes the second core compressor section, the second core combustor section and the second core turbine section, and the second module is configured to be installed with or removed from the second engine core as a complete unit.
7 . The aircraft system of claim 1 , wherein at least one of
the first propulsion system further includes a first module and a first engine core, the first module comprises the first power turbine section, the first engine core includes the first core compressor section, the first core combustor section and the first core turbine section, and the first module is configured to be installed with or removed from the first engine core as a complete unit; or
the second propulsion system further includes a second module and a second engine core, the second module comprises the second power turbine section, the second engine core includes the second core compressor section, the second core combustor section and the second core turbine section, and the second module is configured to be installed with or removed from the second engine core as a complete unit.
8 . The aircraft system of claim 1 , wherein at least one of
the first core turbine rotor is a first intermediate pressure turbine rotor, the first propulsion system further includes a first high pressure turbine rotor also disposed in the first core turbine section, and the first intermediate pressure turbine rotor is disposed between the first high pressure turbine rotor and the first power turbine rotor along the first flowpath; or
the second core turbine rotor is a second intermediate pressure turbine rotor, the second propulsion system further includes a second high pressure turbine rotor also disposed in the second core turbine section, and the second intermediate pressure turbine rotor is disposed between the second high pressure turbine rotor and the second power turbine rotor along the second flowpath.
9 . The aircraft system of claim 1 , wherein at least one of the first power turbine rotor is located axially between the first open propulsor rotor and the first core turbine rotor along the first axis; or the second power turbine rotor is located axially between the second open propulsor rotor and the second core turbine rotor along the second axis.
10 . The aircraft system of claim 1 , wherein at least one of
the first open propulsor rotor is coaxial with the first power turbine rotor; or
the second open propulsor rotor is coaxial with the second power turbine rotor.
11 . The aircraft system of claim 1 , wherein at least one of
the first open propulsor rotor is coaxial with the first core turbine rotor; or
the second open propulsor rotor is coaxial with the second core turbine rotor.
12 . The aircraft system of claim 1 , wherein at least one of the first core turbine rotor is rotatable about a first core axis that is angularly offset from the first axis; or the second core turbine rotor is rotatable about a second core axis that is angularly offset from the second axis.
13 . The aircraft system of claim 1 , wherein at least one of the first core turbine rotor is rotatable about a first core axis that is laterally offset from the first axis; or the second core turbine rotor is rotatable about a second core axis that is laterally offset from the second axis.
14 . The aircraft system of claim 1 , wherein at least one of
the first propulsion system further includes a first geartrain operatively coupling the first power turbine rotor to the first open propulsor rotor; or
the second propulsion system further includes a second geartrain operatively coupling the second power turbine rotor to the second open propulsor rotor.
15 . The aircraft system of claim 1 , wherein at least one of the first propulsion system extends axially along a first centerline axis between a forward end of the first propulsion system and an aft end of the first propulsion system, and the first open propulsor rotor is disposed axially between the forward end of the first propulsion system and the first core combustor section; or the second propulsion system extends axially along a second centerline axis between a forward end of the second propulsion system and an aft end of the second propulsion system, and the second open propulsor rotor is disposed axially between the forward end of the second propulsion system and the second core combustor section.
16 . An aircraft system, comprising:
a first open propulsor rotor;
a first open guide vane structure next to the first open propulsor rotor; and
a first turbine engine including a first core compressor section, a first core combustor section, a first core turbine section, a first power turbine section, a first flowpath, a first core turbine rotor and a first power turbine rotor, the first flowpath extending through the first core compressor section, the first core combustor section, the first core turbine section and the first power turbine section from an inlet into the first flowpath to an exhaust from the first flowpath, the first core turbine rotor disposed in the first core turbine section and configured to rotate in a first rotational direction, the first power turbine rotor disposed in the first power turbine section and configured to rotate in the first rotational direction, and the first power turbine rotor further configured to drive rotation of the first open propulsor rotor in a first propulsor rotational direction about a first axis;
wherein the first power turbine rotor is disposed axially between the first open propulsor rotor and the first core turbine rotor along the first axis, and the first open guide vane structure is selectively rotationally fixed or rotatable about the first axis.
17 . The aircraft system of claim 16 , further comprising:
a second open propulsor rotor;
a second open guide vane structure next to the second open propulsor rotor; and
a second turbine engine including a second core compressor section, a second core combustor section, a second core turbine section, a second power turbine section, a second flowpath, a second core turbine rotor and a second power turbine rotor, the second flowpath extending through the second core compressor section, the second core combustor section, the second core turbine section and the second power turbine section from an inlet into the second flowpath to an exhaust from the second flowpath, the second core turbine rotor disposed in the second core turbine section and configured to rotate in the first rotational direction, the second power turbine rotor disposed in the second power turbine section and configured to rotate in a second rotational direction opposite the first rotational direction, and the second power turbine rotor further configured to drive rotation of the second open propulsor rotor in a second propulsor rotational direction about a second axis that is opposite the first propulsor rotational direction;
wherein the second power turbine rotor is disposed axially between the second open propulsor rotor and the second core turbine rotor along the second axis, and the second open guide vane structure is selectively rotationally fixed or rotatable about the second axis.
18 . The aircraft system of claim 17 , wherein
the first core turbine rotor is a first intermediate pressure turbine rotor;
the first turbine engine further includes a first high pressure turbine rotor also disposed in the first core turbine section; and
the first intermediate pressure turbine rotor is disposed between the first high pressure turbine rotor and the first power turbine rotor along the first flowpath.
19 . An aircraft system, comprising:
a first propulsion system including a first open propulsor rotor, a first core compressor section, a first core combustor section, a first core turbine section, a first power turbine section, a first flowpath, a first core turbine rotor and a first power turbine rotor, the first flowpath extending through the first core compressor section, the first core combustor section, the first core turbine section and the first power turbine section from an inlet into the first flowpath to an exhaust from the first flowpath, the first core turbine rotor disposed in the first core turbine section and configured to rotate in a first rotational direction, the first power turbine rotor disposed in the first power turbine section and configured to rotate in the first rotational direction, and the first power turbine rotor operatively coupled to the first open propulsor rotor; and
a second propulsion system including a second open propulsor rotor, a second core compressor section, a second core combustor section, a second core turbine section, a second power turbine section, a second flowpath, a second core turbine rotor and a second power turbine rotor, the second flowpath extending through the second core compressor section, the second core combustor section, the second core turbine section and the second power turbine section from an inlet into the second flowpath to an exhaust from the second flowpath, the second core turbine rotor disposed in the second core turbine section and configured to rotate in the first rotational direction, the second power turbine rotor disposed in the second power turbine section and configured to rotate in a second rotational direction that is opposite the first rotational direction, and the second power turbine rotor operatively coupled to the second open propulsor rotor;
wherein at least one of
the first open propulsor rotor is rotatable about a first axis, and the first core turbine rotor is located axially between the first open propulsor rotor and the first power turbine rotor along the first axis; or
the second open propulsor rotor is rotatable about a second axis, and the second core turbine rotor is located axially between the second open propulsor rotor and the second power turbine rotor along the second axis.