Granted Patent B2

US 12,735,189 · App. 19/016,778 · Granted Sep 15, 2026

Inventors: Jeffrey T. Morton (Manchester, CT); Jon E. Sobanski (Glastonbury, CT); Andrew E. Breault (Bolton, CT)

Assignee: RTX Corporation

B64D27/20B64D27/18F01D15/10F05D2260/4031

Abstract

Claims (70)

1 . An assembly for an aircraft, comprising:

a first propulsion system and a second propulsion system;

each of the first propulsion system and the second propulsion system including an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor, the open propulsor rotor comprising a plurality of open propulsor blades, the turbine engine including a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath, the first rotating structure comprising a first bladed rotor, the second rotating structure comprising a second bladed rotor and operable to rotate independent of the first rotating structure, and the flowpath extending through the compressor section, the combustor section and the turbine section with the first bladed rotor disposed between the second bladed rotor and the combustor section along the flowpath;

wherein the open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction and has a first propulsor rotation parameter equal to positive one;

wherein the open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction, that is opposite the first rotational direction, and has a second propulsor rotation parameter equal to negative one;

wherein the first bladed rotor of the first propulsion system has a first system first rotor rotation parameter equal to positive one where the first bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;

wherein the first bladed rotor of the second propulsion system has a second system first rotor rotation parameter equal to positive one where the first bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;

wherein the second bladed rotor of the first propulsion system has a first system second rotor rotation parameter equal to positive one where the second bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;

wherein the second bladed rotor of the second propulsion system has a second system second rotor rotation parameter equal to positive one where the second bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the second propulsion system is configured to rotate in the second rotational direction; and

wherein a sum of the first propulsor rotation parameter, the second propulsor rotation parameter, the first system first rotor rotation parameter, the second system first rotor rotation parameter, the first system second rotor rotation parameter and the second system second rotor rotation parameter is equal to zero.

2 . The assembly of claim 1 , wherein the first bladed rotor of the first propulsion system and the first bladed rotor of the second propulsion system are configured to rotate in a common rotational direction.

3 . The assembly of claim 1 , wherein the first bladed rotor of the first propulsion system and the first bladed rotor of the second propulsion system are configured to rotate in opposite rotational directions.

4 . The assembly of claim 1 , wherein the second bladed rotor of the first propulsion system and the second bladed rotor of the second propulsion system are configured to rotate in a common rotational direction.

5 . The assembly of claim 1 , wherein the second bladed rotor of the first propulsion system and the second bladed rotor of the second propulsion system are configured to rotate in opposite rotational directions.

6 . The assembly of claim 1 , wherein

the first bladed rotor of each of the first propulsion system and the second propulsion system comprises a first bladed compressor rotor; and

the second bladed rotor of each of the first propulsion system and the second propulsion system comprises a second bladed compressor rotor.

7 . The assembly of claim 1 , wherein

the first bladed rotor of each of the first propulsion system and the second propulsion system comprises a first bladed turbine rotor; and

the second bladed rotor of each of the first propulsion system and the second propulsion system comprises a second bladed turbine rotor.

8 . The assembly of claim 1 , wherein

the first bladed rotor of the first propulsion system is next to the second bladed rotor of the first propulsion system along the flowpath of the first propulsion system; and

the first bladed rotor of the second propulsion system is next to the second bladed rotor of the second propulsion system along the flowpath of the second propulsion system.

9 . The assembly of claim 1 , wherein

the second rotating structure of the first propulsion system is operatively coupled to and configured to drive the rotation of the open propulsor rotor of the first propulsion system; and

the second rotating structure of the second propulsion system is operatively coupled to and configured to drive the rotation of the open propulsor rotor of the second propulsion system.

10 . The assembly of claim 1 , wherein

the turbine engine of the first propulsion system further includes a first engine third rotating structure operatively coupled to the open propulsor rotor of the first propulsion system, the first engine third rotating structure comprises a first engine third structure bladed rotor disposed within the turbine section of the first propulsion system, the first engine third structure bladed rotor has a first system third rotor rotation parameter equal to positive one where the first engine third structure bladed rotor is configured to rotate in the first rotational direction or negative one where the first engine third structure bladed rotor is configured to rotate in the second rotational direction;

the turbine engine of the second propulsion system further includes a second engine third rotating structure operatively coupled to the open propulsor rotor of the second propulsion system, the second engine third rotating structure comprises a second engine third structure bladed rotor disposed within the turbine section of the second propulsion system, the second engine third structure bladed rotor has a second system third rotor rotation parameter equal to positive one where the second engine third structure bladed rotor is configured to rotate in the first rotational direction or negative one where the second engine third structure bladed rotor is configured to rotate in the second rotational direction; and

an absolute value of a sum of the first propulsor rotation parameter, the second propulsor rotation parameter, the first system first rotor rotation parameter, the second system first rotor rotation parameter, the first system second rotor rotation parameter, the second system second rotor rotation parameter, the first system third rotor rotation parameter and the second system third rotor rotation parameter is equal to or less than two.

11 . The assembly of claim 10 , wherein the sum of the first propulsor rotation parameter, the second propulsor rotation parameter, the first system first rotor rotation parameter, the second system first rotor rotation parameter, the first system second rotor rotation parameter, the second system second rotor rotation parameter, the first system third rotor rotation parameter and the second system third rotor rotation parameter is equal to zero.

12 . The assembly of claim 1 , wherein the turbine engine of each of the first propulsion system and the second propulsion system is configured as a two-spool engine.

13 . The assembly of claim 1 , wherein the turbine engine of each of the first propulsion system and the second propulsion system is configured as a three-spool engine.

14 . The assembly of claim 1 , wherein each of the first propulsion system and the second propulsion system further includes an open guide vane structure next to the open propulsor rotor.

15 . The assembly of claim 1 , wherein each of the first propulsion system and the second propulsion system further includes a geared drivetrain operatively coupling the open propulsor rotor to the turbine engine.

16 . The assembly of claim 1 , further comprising:

an aircraft airframe comprising an aircraft fuselage;

the first propulsion system and the second propulsion system mounted to the aircraft airframe and arranged to opposing lateral sides of the aircraft fuselage.

17 . The assembly of claim 1 , wherein the open propulsor rotor of each of the first propulsion system and the second propulsion system comprises at least twelve of the open propulsor blades.

18 . An assembly for an aircraft, comprising:

a first propulsion system and a second propulsion system;

each of the first propulsion system and the second propulsion system including an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor, the open propulsor rotor comprising a plurality of open propulsor blades, the turbine engine including a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath, the first rotating structure comprising a first bladed rotor, the second rotating structure comprising a second bladed rotor and operable to rotate independent of the first rotating structure, and the flowpath extending through the compressor section, the combustor section and the turbine section with the first bladed rotor disposed between the second bladed rotor and the combustor section along the flowpath;

wherein the open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction and has a first propulsor rotation parameter equal to positive one;

wherein the open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction, that is opposite the first rotational direction, and has a second propulsor rotation parameter equal to negative one;

wherein the first bladed rotor of the first propulsion system has a first system first rotor rotation parameter equal to positive one where the first bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;

wherein the first bladed rotor of the second propulsion system has a second system first rotor rotation parameter equal to positive one where the first bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;

wherein the second bladed rotor of the first propulsion system has a first system second rotor rotation parameter equal to positive one where the second bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;

wherein the second bladed rotor of the second propulsion system has a second system second rotor rotation parameter equal to positive one where the second bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;

wherein a product of the first propulsor rotation parameter, the first system first rotor rotation parameter and the first system second rotor rotation parameter is equal to a first value;

wherein a product of the second propulsor rotation parameter, the second system first rotor rotation parameter and the second system second rotor rotation parameter is equal to a second value; and

wherein a sum of the first value and the second value is equal to zero.

19 . The assembly of claim 18 , wherein

the turbine engine of the first propulsion system further includes a first engine third rotating structure operatively coupled to the open propulsor rotor of the first propulsion system, the first engine third rotating structure comprises a first engine third structure bladed rotor disposed within the turbine section of the first propulsion system, the first engine third structure bladed rotor has a first system third rotor rotation parameter equal to positive one where the first engine third structure bladed rotor is configured to rotate in the first rotational direction or negative one where the first engine third structure bladed rotor is configured to rotate in the second rotational direction;

the turbine engine of the second propulsion system further includes a second engine third rotating structure operatively coupled to the open propulsor rotor of the second propulsion system, the second engine third rotating structure comprises a second engine third structure bladed rotor disposed within the turbine section of the second propulsion system, the second engine third structure bladed rotor has a second system third rotor rotation parameter equal to positive one where the second engine third structure bladed rotor is configured to rotate in the first rotational direction or negative one where the second engine third structure bladed rotor is configured to rotate in the second rotational direction;

a product of the first propulsor rotation parameter, the first system first rotor rotation parameter, the first system second rotor rotation parameter and the first system third rotor rotation parameter is equal to a third value;

a product of the second propulsor rotation parameter, the second system first rotor rotation parameter, the second system second rotor rotation parameter and the second system third rotor rotation parameter is equal to a fourth value; and

a sum of the third value and the fourth value is equal to zero.

20 . An assembly for an aircraft, comprising:

a first propulsion system and a second propulsion system;

each of the first propulsion system and the second propulsion system including an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor, the turbine engine including a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath, the first rotating structure comprising a first bladed rotor, the second rotating structure comprising a second bladed rotor and operable to rotate independent of the first rotating structure, and the flowpath extending through the compressor section, the combustor section and the turbine section with the first bladed rotor disposed between the second bladed rotor and the combustor section along the flowpath;

wherein the open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction and has a first propulsor rotation parameter equal to positive one;

wherein the open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction, that is opposite the first rotational direction, and has a second propulsor rotation parameter equal to negative one;

wherein the first bladed rotor of the first propulsion system has a first system first rotor rotation parameter equal to positive one where the first bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;

wherein the first bladed rotor of the second propulsion system has a second system first rotor rotation parameter equal to positive one where the first bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;

wherein the second bladed rotor of the first propulsion system has a first system second rotor rotation parameter equal to positive one where the second bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;

wherein the second bladed rotor of the second propulsion system has a second system second rotation parameter equal to positive one where the second bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;

wherein an absolute value of a sum of the first propulsor rotation parameter, the second propulsor rotation parameter, the first system first rotor rotation parameter, the second system first rotor rotation parameter, the first system second rotor rotation parameter and the second system second rotor rotation parameter is equal to or less than two;

wherein a product of the first propulsor rotation parameter, the first system first rotor rotation parameter and the first system second rotor rotation parameter is equal to a first value;

wherein a product of the second propulsor rotation parameter, the second system first rotor rotation parameter and the second system second rotor rotation parameter is equal to a second value; and

wherein a sum of the first value and the second value is equal to zero.

Assignments (1)

Continuity (1)

References Cited (27)