Gearbox efficiency rating for turbomachine engines
US-11473507-B2 · Oct 18, 2022 · US
Overall engine efficiency rating for turbomachine engines
US2024263588A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2024263588-A1 |
| Application number | US-202418606371-A |
| Country | US |
| Kind code | A1 |
| Filing date | Mar 15, 2024 |
| Priority date | Jan 31, 2022 |
| Publication date | Aug 8, 2024 |
| Grant date | — |
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Abstract
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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.
First claim
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1 . 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 low-pressure turbine, wherein the low-pressure turbine is configured to rotate at a rotational speed of 2,500 to 15,000 rpm at a cruise flight condition; a gearbox including an input and an output, wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, wherein the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio (GR) of the first rotational speed to the second rotational speed is within a range of 2.0-4.0; and an overall engine efficiency rating greater than or equal to 1.9 and less than or equal to GR 1.5 , wherein the overall engine efficiency rating equals Q ( D 1.56 T ) 1.53 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. 2 . The turbomachine engine of claim 1 , wherein the low-pressure turbine is configured to rotate at a rotational speed of 5,000 to 10,000 rpm at the cruise flight condition. 3 . The turbomachine engine of claim 1 , wherein the fan assembly comprises 8-20 fan blades. 4 . The turbomachine engine of claim 1 , wherein the D is within a range of 84-120 inches. 5 . The turbomachine engine of claim 1 , the fan assembly can be configured to rotate at a rotational speed of 700-1500 rpm at the cruise flight condition. 6 . The turbomachine engine of claim 1 , the fan assembly can be configured to rotate at a rotational speed of 850-1350 rpm at the cruise flight condition. 7 . 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 low-pressure turbine, wherein the low-pressure turbine is configured to rotate at a rotational speed of 2,500 to 15,000 rpm at a cruise flight condition; a gearbox including an input and an output, wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, wherein the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio (GR) of the first rotational speed to the second rotational speed is within a range of 2.0-4.0; and an overall engine efficiency rating greater than or equal to 0.1 GR 1.5 and less than or equal to GR 1.5 , wherein the overall engine efficiency rating equals Q ( D 1.56 T ) 1.53 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. 8 . The turbomachine engine of claim 7 , wherein the low-pressure turbine is configured to rotate at a rotational speed of 5,000 to 10,000 rpm at the cruise flight condition. 9 . The turbomachine engine of claim 7 , wherein the fan assembly comprises 8-20 fan blades. 10 . The turbomachine engine of claim 7 , wherein the D is within a range of 84-120 inches. 11 . The turbomachine engine of claim 7 , the fan assembly can be configured to rotate at a rotational speed of 700-1500 rpm at the cruise flight condition. 12 . The turbomachine engine of claim 7 , the fan assembly can be configured to rotate at a rotational speed of 850-1350 rpm at the cruise flight condition. 13 . 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 low-pressure turbine, wherein the low-pressure turbine is configured to rotate at a rotational speed of 2,500 to 15,000 rpm at a cruise flight condition; a gearbox including an input and an output, wherein the input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, wherein the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio (GR) of the first rotational speed to the second rotational speed is within a range of 2.0-4.0; and an overall engine efficiency rating greater than or equal to 0.1 GR 1.5 and less than or equal to GR 1.5 , wherein the overall engine efficiency rating equals Q ( D 1.56 T ) 1.53 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
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Lubrication · CPC title
of the epicyclical, planetary or differential type · CPC title
Square power · CPC title
Division · CPC title
Product · CPC title
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- What does patent US2024263588A1 cover?
- 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 …
- Who is the assignee on this patent?
- Gen Electric, Ge Avio Srl
- What technology area does this patent fall under?
- Primary CPC classification F02C7/36. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Aug 08 2024 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).