Dual fan gas turbine engine and gear train

Patent metadata

Field	Value
Publication number	US-10151248-B2
Application number	US-201113340838-A
Country	US
Kind code	B2
Filing date	Dec 30, 2011
Priority date	Oct 3, 2007
Publication date	Dec 11, 2018
Grant date	Dec 11, 2018

Abstract

A gas turbine engine includes a first fan, a second fan spaced axially from the first fan, a turbine-driven fan shaft and an epicyclic gear train coupled to be driven by the turbine-driven fan shaft and coupled to drive the first fan and the second fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. The star gears are supported on respective journal bearings.

First claim

What is claimed is:

1. A turbine engine comprising:
a first fan;
a second fan spaced axially from the first fan;
a turbine-driven fan shaft; and
an epicyclic gear train that is coupled to be driven by the turbine-driven fan shaft and that is coupled to drive the first fan and the second fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, the intermediate gears being supported on respective journal bearings, wherein the epicyclic gear train has a gear reduction ratio such that ω Second-stage =ω First-stage ×[(NR+Ns)/NR], where ω First-stage is a rotational speed of the first fan, ω Second-stage is a rotational speed of the second fan, NR is the number of teeth on the ring gear and NS is the number of teeth on the sun gear.

2. The turbine engine as recited in claim 1 , wherein the epicyclic gear train is coupled to directly drive the second fan without a rotational speed change relative to the turbine-driven fan shaft and coupled to drive the first fan at a reduced rotational speed relative to the turbine-driven fan shaft.

3. The turbine engine as recited in claim 1 , wherein the first fan is coupled to be driven from the carrier and the second fan is coupled to be driven from the ring gear.

4. The turbine engine as recited in claim 1 , wherein the epicyclic gear train has a gear reduction ratio of greater than or equal to 2.3.

5. The turbine engine as recited in claim 1 , wherein the epicyclic gear train has a gear reduction ratio of greater than or equal to 2.5.

6. The turbine engine as recited in claim 1 , wherein the epicyclic gear train has a gear reduction ratio of about 1.37:1.

7. The turbine engine as recited in claim 1 , wherein the first fan and the second fan define a bypass ratio of greater than ten (10) with regard to a bypass airflow and a core airflow.

8. The turbine engine as recited in claim 1 , wherein the first fan and the second fan define an overall fan pressure ratio that is that is from 1 to 1.45.

9. The turbine engine as recited in claim 1 , wherein the ring gear is a rotatable input, the sun gear is fixed, and the carrier is a rotatable output, and wherein the carrier is coupled with a first-stage shaft, the first-stage shaft is coupled with the first fan, the ring gear is coupled at a common connection to the turbine-driven shaft and a second-stage shaft, and the second-stage shaft is coupled with the second fan.

10. The turbine engine as recited in claim 9 , wherein the first fan and the second fan are coupled to be driven in a common rotational direction.

11. The turbine engine as recited in claim 1 , further comprising a bypass duct, and the first fan and the second fan are in the bypass duct.

12. The turbine engine as recited in claim 11 , wherein the first fan and the second fan are, at least in part, both axially forward of the epicyclic gear train.

13. A turbine engine comprising:
a bypass duct;
a forward fan and an aft fan in the bypass duct;
a turbine-driven shaft; and
an epicyclic gear train through which the turbine-driven shaft is coupled such that the aft fan is rotatable through the epicyclic gear train at a first speed and the forward fan is rotatable through the epicyclic gear train at a second speed that is lower than the first speed, wherein the forward fan and the aft fan are rotatable in a common rotational direction.

14. The turbine engine as recited in claim 13 , wherein the epicyclic gear train has a gear reduction ratio of greater than or equal to 2.3.

15. The turbine engine as recited in claim 13 , wherein the epicyclic gear train has a gear reduction ratio of greater than or equal to 2.5.

16. The turbine engine as recited in claim 13 , wherein the epicyclic gear train has a gear reduction ratio of greater than or equal to 1.37.

17. The turbine engine as recited in claim 13 , wherein the epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear, a ring gear surrounding and meshing with the intermediate gears, and the intermediate gears are supported on respective journal bearings, and wherein the ring gear is a rotatable input, the sun gear is fixed, and the carrier is a rotatable output.

18. The turbine engine as recited in claim 17 , wherein the carrier is coupled with a first-stage shaft, the first-stage shaft is coupled with the forward fan, the ring gear is coupled at a common connection to the turbine-driven shaft and a second-stage shaft, and the second-stage shaft is coupled with the aft fan.

Assignees

• Sheridan William G
• United Technologies Corp

Inventors

• Sheridan William G

Classifications

• F02C7/36 Primary

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F16H57/082

  Planet carriers · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title