DUAL TOWER SHAFT GEARBOX FOR GAS TURBINE ENGINE

• US 20160169118A1
• Filed: 11/20/2015
• Published: 06/16/2016
• Est. Priority Date: 12/12/2014
• Status: Abandoned Application

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Duong, Hung
• Application Number:
  US14/947,441
• Publication Number:
  US 20160169118A1
• Time in Patent Office: Days
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 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 Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2230/644 for adjusting the position or the alignment, e.g. wedges or eccenters
• CPC Class Codes: F05D 2240/40 Use of a multiplicity of similar components
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2260/4031 as in toothed gearing

Abstract

A gas turbine engine includes a turbine section that has first and second turbines mounted for rotation about a common rotational axis within an engine static structure. First and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted. First and second tower shafts respectively coupled to the first and second turbine shafts. An accessory drive gearbox is mounted to the engine static structure. The accessory drive gearbox includes gears arranged within a common housing. The first and second tower shafts extend into the common housing and are coupled to the gears.

Claims

1. A gas turbine engine comprising:

a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure;

first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted;

first and second tower shafts respectively coupled to the first and second turbine shafts; and

an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including gears arranged within a common housing, the first and second tower shafts extending into the common housing and coupled to the gears.

2. The gas turbine engine according to claim 1, wherein the first and second turbine shafts are inner and outer shafts, respectively, and the first and second turbines are low and high pressure turbines, respectively.

3. The gas turbine engine according to claim 2, wherein the second tower shaft is configured to rotate at a higher speed than the first tower shaft.

4. The gas turbine engine according to claim 2, wherein a first set of accessories are configured to be rotationally driven by the first tower shaft, and a second set of accessories are configured to be rotationally driven by the second tower shaft.

5. The gas turbine engine according to claim 4, wherein the first set of accessories includes at least one of a generator, a deoiler and a hydraulic pump.

6. The gas turbine engine according to claim 4, wherein the second set of accessories includes at least one of a generator, a fuel pump, an oil pump and a permanent magnet alternator.

7. The gas turbine engine according to claim 1, wherein the first and second tower shafts extend in a generally radial direction from the rotational axis, the first and second tower shafts arranged at an angle circumferentially relative to one another.

8. The gas turbine engine according to claim 7, wherein the angle is less than 90°

.

9. The gas turbine engine according to claim 1, wherein the gears include first and second sets of gears respectively coupled to the first and second tower shafts, the first set of gears is not in meshing engagement with the second set of gears.

10. The gas turbine engine according to claim 9, wherein at least a portion of the first and second sets of gears circumferentially overlap one another.

11. The gas turbine engine according to claim 1, wherein the housing includes a locating feature configured to circumferentially locate and align at least one of the first and second tower shafts relative to at least one of the first and second turbine shafts.

12. The gas turbine engine according to claim 11, wherein the locating feature includes a bore and a first cover that has an eccentric pilot received in the bore, the first cover includes a hole and is rotatable within the bore to reposition the hole relative to the housing, the hole supporting one of the first and second tower shafts.

13. The gas turbine engine according to claim 12, wherein the housing includes a second cover opposite the first cover and configured to facilitate insertion of one of the first and second tower shafts into the housing during assembly.

14. A method of installing an accessory gearbox onto a gas turbine engine, the method comprising the steps of:

mounting a gearbox housing onto an engine static structure, the gearbox housing having first and second opposing sides;

inserting a first tower shaft into the first side of the housing, through the second side, and into the engine static structure to couple the first tower shaft with a first turbine shaft in the static structure and a first gear set in the gearbox housing; and

inserting a second tower shaft into the first side of the housing, through the second side, and into the engine static structure to couple the second tower shaft with a second turbine shaft in the static structure and a second gear set in the gearbox housing.

15. The method according to claim 14, wherein the first set of gears is not in meshing engagement with the second set of gears.

16. The method according to claim 14, comprising the step of adjusting a position of a locating feature to circumferentially locate and align at least one of the first and second tower shafts relative to at least one of the first and second turbine shafts.

17. The method according to claim 14, comprising a turbine section having first and second turbines mounted for rotation about a common rotational axis within the engine static structure, the first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, wherein the first and second turbine shafts are inner and outer shafts, respectively, and the first and second turbines are low and high pressure turbines, respectively, wherein the second tower shaft is configured to rotate at a higher speed than the first tower shaft.

18. The method according to claim 14, wherein the inserting steps include installing the first and second tower shafts in a generally radial direction relative to the rotational axis, the first and second tower shafts at an acute angle circumferentially relative to one another.

19. The method according to claim 14, comprising the step of mounting first and second sets of accessories to the gearbox, wherein the first set of accessories includes at least one of a generator, a deoiler and a hydraulic pump, and the second set of accessories includes at least one of a generator, a fuel pump, an oil pump and a permanent magnet alternator.