Overall engine efficiency rating for turbomachine engines
AssigneesGE Avio S.r.l., General Electric Company
InventorsAndrea Piazza, Jeffrey D. Clements
Life of this patent
Estimating the term…
Abstract
A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.
Claims18
A turbomachine engine comprising:
- a fan assembly including a plurality of fan blades;
- a vane assembly including a plurality of vanes disposed aft of the plurality of fan blades;
- a core engine including a low-pressure turbine;
- a gearbox including an input, an output, and a gear ratio (GR), wherein the gearbox is a multi-stage gearbox, wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine, and wherein the output of the gearbox is coupled to the fan assembly;
- and
- an overall engine efficiency rating greater than or equal to 1.9 and less than or equal to GR1.5, wherein the overall engine efficiency rating equals
- Q
-
- (
- D
- 1.56
- T
- )
- 1
- .
- 5
-
- 3
-
- N
- 2
- ,
- wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition, and wherein N is a number of rotating blade stages of the low-pressure turbine.
A turbomachine engine comprising:
- a fan assembly including a plurality of fan blades;
- a vane assembly including a plurality of vanes disposed aft of the plurality of fan blades;
- a core engine including a low-pressure turbine;
- a gearbox including an input, an output, and a gear ratio (GR), wherein the gearbox is a multi-stage gearbox, wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine, and wherein the output of the gearbox is coupled to the fan assembly;
- and
- an overall engine efficiency rating greater than or equal to 0.1GR1.5 and less than or equal to GR1.5, wherein the overall engine efficiency rating equals
- Q
-
- (
- D
- 1.56
- T
- )
- 1
- .
- 5
-
- 3
-
- N
- 2
- ,
- wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition, and wherein N is a number of rotating blade stages of the low-pressure turbine.
A turbomachine engine comprising:
- a fan assembly including a plurality of fan blades;
- a vane assembly including a plurality of vanes disposed aft of the plurality of fan blades;
- a core engine including a low-pressure turbine;
- a gearbox including an input, an output, and a gear ratio (GR), wherein the gearbox is a multi-stage gearbox, wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine, and wherein the output of the gearbox is coupled to the fan assembly;
- and
- an overall engine efficiency rating greater within a range of 0.57-8.0, wherein the overall engine efficiency rating equals
- Q
-
- (
- D
- 1.56
- T
- )
- 1
- .
- 5
-
- 3
-
- N
- 2
- ,
- wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition, and wherein N is a number of rotating blade stages of the low-pressure turbine.
Dependencies are inferred from the claim text.