Gearbox for gas turbine engine
A gearbox for an aircraft engine including first and second gears in driving engagement through planet gears supported by a carrier. Selective application of a brake and a blocking member permit operation in a speed change configuration and a direct drive configuration.
1. A gearbox for a gas turbine engine, the gearbox comprising:
a gear assembly including first and second gears in driving engagement through planet gears, the planet gears rotatable about a respective central axis and supported by a carrier, the assembly connected to input and output shafts and including at least one rotatable intermediate component;
a brake configured to selectively impede rotation of the intermediate component; and
a blocking member configured to selectively impede rotation of the planet gears about the central axes;
wherein the gearbox is selectively configurable between:
a speed change configuration wherein the brake is configured to impede the rotation of the intermediate component and the blocking member is configured to allow the rotation of the planet gears about the central axes to define a speed ratio different than 1 between rotational speeds of the input and output shafts; and
a direct drive configuration wherein the brake is configured to allow the rotation of the intermediate component and the blocking member is configured to impede the rotation of the planet gears about the central axes so that the input and output shafts are rotatable together at a same rotational speed.
2. The gearbox as defined in claim 1 , wherein the blocking member is a clutch selectively interconnecting the output shaft to the intermediate component so that the output shaft and the intermediate component are rotatable together at the same rotational speed, the output shaft and the intermediate component rotatable together at the same rotational speed preventing the rotation of the planet gears about the central axes.
3. The gearbox as defined in claim 2 , wherein the first gear is connected to the input shaft and is configured as a ring gear, the second gear is connected to the output shaft and is configured as a sun gear, the intermediate component is the carrier, and the planet gears include a first set of planet gears in meshed engagement with the first gear and a second set of planet gears in meshed engagement with the second gear, corresponding planet gears of the first and second sets being meshed together.
4. The gearbox as defined in claim 2 , wherein the first gear is connected to the input shaft and is configured as a ring gear, the carrier is connected to the output shaft, and the intermediate component is the second gear and is configured as a sun gear.
5. The gearbox as defined in claim 2 , wherein the first gear is connected to the input shaft and is configured as a first sun gear, the second gear is connected to the output shaft and is configured as a second sun gear, and the intermediate component is the carrier, the planet gears including pairs of first and second interconnected planet gears rotatable together, the first planet gears in meshed engagement with the first sun gear and the second planet gears in meshed engagement with the second sun gear.
6. The gearbox as defined in claim 1 , wherein the blocking member is a brake selectively engageable to the planet gears.
7. The gearbox as defined in claim 1 , wherein the input and output shafts are coaxial.
8. A gas turbine engine comprising:
an input shaft drivingly engaged to a turbine rotor;
an output shaft drivingly engaged to a drivable rotor; and
a gearbox including first and second gears in driving engagement through planet gears, the planet gears rotatable about a respective central axis and supported by a carrier, wherein: one of the first gear, second gear and carrier is connected to the input shaft, another one of the first gear, second gear and carrier is connected to the output shaft, and a remaining one of the first gear, second gear and carrier is an intermediate component, the gearbox further including a brake and a blocking member, the brake selectively movable between a brake position impeding rotation of the intermediate component and a release position allowing rotation of the intermediate component, the blocking member selectively movable between an engaged position impeding rotation of the planet gears about the central axes and a disengaged position allowing rotation of the planet gears about the central axes;
wherein the gearbox is selectively configurable between:
a direct drive configuration where the brake is in the release position and the blocking member is in the engaged position, and
a speed change configuration where the brake is in the brake position and the blocking member is in the disengaged position.
9. The gas turbine engine as defined in claim 8 , wherein the drivable rotor is a compressor rotor.
10. The gas turbine engine as defined in claim 9 , wherein the turbine rotor is a low pressure turbine rotor and the compressor rotor is a boost compressor rotor, and the gas turbine engine further comprises a high pressure turbine rotor rotatable independently of the input shaft and located upstream of the low pressure turbine rotor.
11. The gas turbine engine as defined in claim 8 , wherein the drivable rotor is a propeller.
12. The gas turbine engine as defined in claim 8 , wherein the blocking member is a clutch selectively interconnecting the output shaft to the intermediate component so that the output shaft and the intermediate component are rotatable together at the same rotational speed, the output shaft and the intermediate component rotatable together at the same rotational speed preventing the rotation of the planet gears about the central axes.
13. The gas turbine engine as defined in claim 12 , wherein the first gear is connected to the input shaft and is configured as a ring gear, the second gear is connected to the output shaft and is configured as a sun gear, the intermediate component is the carrier, and the planet gears include a first set of planet gears in meshed engagement with the first gear and a second set of planet gears in meshed engagement with the second gear, corresponding planet gears of the first and second sets being meshed together.
14. The gas turbine engine as defined in claim 12 , wherein the first gear is connected to the input shaft and is configured as a ring gear, the carrier is connected to the output shaft, and the intermediate component is the second gear and is configured as a sun gear.
15. The gas turbine engine as defined in claim 12 , wherein the first gear is connected to the input shaft and is configured as a first sun gear, the second gear is connected to the output shaft and is configured as a second sun gear, and the intermediate component is the carrier, the planet gears including pairs of first and second interconnected planet gears rotatable together, the first planet gears in meshed engagement with the first sun gear and the second planet gears in meshed engagement with the second sun gear.
16. The gas turbine engine as defined in claim 8 , wherein the blocking member is a brake selectively engageable to the planet gears.
17. The gas turbine engine as defined in claim 8 , wherein the input and output shafts are coaxial.
18. A method of rotating a rotor of a gas turbine engine through a gearbox including first and second gears drivingly interconnected by rotatable planet gears supported by a carrier, the method comprising:
rotating an input shaft with a turbine section of the gas turbine engine;
rotating one of the first gear, the second gear and the carrier with the input shaft while another one of the first gear, the second gear and the carrier is connected to an output shaft and a remaining one of the first gear, the second gear and the carrier is an intermediate component;
configuring the gearbox in a selected one of a direct drive configuration and a speed change configuration, including:
when the direct drive configuration is selected, preventing rotation of the planet gears while allowing rotation of the intermediate component so that the input and output shafts rotate together as a single shaft at a same rotational speed, and
when the second configuration is selected, preventing rotation of the intermediate component while allowing rotation of the planet gears so that the input and output shafts rotate at different rotational speeds; and
driving the output shaft with the input shaft through the gearbox, and rotating the rotor with the output shaft.
19. The method as defined in claim 18 , wherein the rotor is part of a low pressure compressor section of the gas turbine engine.
20. The method as defined in claim 18 , wherein the rotor is a propeller.