Mechanical drive architectures with hybrid-type low-loss bearings and low-density materials

Patent metadata

Field	Value
Publication number	US-2016363003-A1
Application number	US-201414460620-A
Country	US
Kind code	A1
Filing date	Aug 15, 2014
Priority date	Aug 15, 2014
Publication date	Dec 15, 2016
Grant date	—

Abstract

Mechanical drive architectures can include a gas turbine having a compressor section, a turbine section, and a combustor section. A load compressor is driven by the gas turbine. A rotor shaft extends through the gas turbine and the load compressor. The rotor shaft has rotating blades arranged in a circumferential array to define a plurality of moving blade rows in the gas turbine and the load compressor. At least one of the rotating blades in one of the gas turbine and the load compressor includes a low-density material. Bearings support the rotor shaft within the gas turbine and the load compressor, wherein at least one of the bearings is a hybrid-type low-loss bearing.

First claim

What is claimed is:

1 . A mechanical drive architecture, comprising:
a gas turbine having a compressor section, a turbine section, and a combustor section operatively coupled to the compressor section and the turbine section; a load compressor driven by the gas turbine; a rotor shaft extending through the compressor section and the turbine section of the gas turbine and the load compressor; and a plurality of bearings to support the rotor shaft within the gas turbine and the load compressor, wherein at least one of the bearings is a hybrid-type low-loss bearing; and wherein the compressor section, the turbine section, and the load compressor each have a plurality of rotating components, at least one of the rotating components in at least one of the compressor section, the turbine section, and the load compressor including a low-density material.

2 . The mechanical drive architecture of claim 1 , further comprising at least one mono-type low-loss bearing including a very low viscosity fluid.

3 . The mechanical drive architecture of claim 1 , further comprising at least one oil bearing.

4 . The mechanical drive architecture of claim 1 , wherein the rotor shaft includes a single shaft arrangement.

5 . The mechanical drive architecture of claim 1 , further comprising a reheat section operatively coupled to the turbine section along the rotor shaft, the reheat section having a reheat combuster section and a reheat turbine section wity a plurality of rotating components; wherein at least one of the rotating components in the compressor section, the turbine section, the load compressor, and the reheat turbine section includes the low-density material.

6 . The mechanical drive architecture of claim 1 , wherein the gas turbine comprises a rear-end drive gas turbine.

7 . The mechanical drive architecture of claim 1 , further comprising a load coupling element for coupling the load compressor to the gas turbine along the rotor shaft.

8 . The mechanical drive architecture of claim 1 , wherein the rotor shaft includes a multi-shaft arrangement having a first rotor shaft extending through the compressor section and the turbine section and a second rotor shaft extending through the load compressor, each of the first rotor shaft and the second rotor shaft being supported by the plurality of bearings.

9 . The mechanical drive architecture of claim 8 , further comprising a gearbox assembly configured to rotate the rotating components in the gas turbine at a different rotational speed than the rotating components in the load compressor.

10 . The mechanical drive architecture of claim 8 , further comprising a power turbine section coupled to the second rotor shaft to drive the load compressor; wherein the power turbine section has a plurality of rotating components, at least one of the rotating components in the compressor section, the turbine section, the load compressor, and the power turbine section including the low-density material.

11 . The mechanical drive architecture of claim 10 , further comprising a reheat section operatively coupled to the turbine section along the first rotor shaft, the reheat section having a reheat combustor section and a reheat turbine section with a plurality of rotating components; wherein at least one of the rotating components in the compressor section, the turbine section, the load compressor, the power turbine section, and the reheat turbine section includes the low-density material.

12 . The mechanical drive architecture of claim 1 , wherein the compressor section of the gas turbine includes forward stages distal to the combustor section, aft stages proximate to the combustor section, and mid stages disposed therebetween;
wherein the forward stages, the mid stages, and the aft stages have a plurality of rotating components; wherein at least one of the rotating components in the forward stages of the compressor section, the mid stages of the compressor section, the aft stages of the compressor section, the turbine section, and the load compressor includes the low-density material; wherein the mechanical drive architecture further includes a stub shaft radially outward of the rotor shaft and extending through the forward stages, such that the rotating components of the forward stages arranged about the stub shaft operate a slower rotational speed than the rotating components of the mid and aft stages arranged about the rotor shaft.

13 . The mechanical drive architecture of claim 12 , wherein the plurality of bearings includes stub shaft bearings to support the stub shaft, at least one of the stub shaft bearings includes a hybrid-type low-loss bearing.

14 . The mechanical drive architecture of claim 1 , wherein the compressor section includes a low pressure compressor section and a high pressure compressor section, and the turbine section includes a low pressure turbine section and a high pressure compressor section and the low pressure turbine section drives the low pressure compressor section.

15 . The mechanical drive architecture of claim 14 , wherein each of the low pressure compressor section, the high pressure compressor section, the low pressure turbine section, the high pressure turbine section includes a plurality of rotating components; and wherein at least one of the rotating components in the low pressure compressor section, the high pressure compressor section, the low pressure turbine section, the high pressure turbine section, and the load compressor includes the low-density material.

16 . The mechanical drive architecture of claim 14 , wherein the rotor shaft includes a dual spool arrangement having a low-speed spool and a high-speed spool, the low-speed spool including the low pressure turbine section and the low pressure compressor section, and the high-speed spool including the high pressure turbine section and the high pressure compressor section.

17 . The mechanical drive architecture of claim 16 , wherein the low speed spool and the high speed spool are supported by the plurality of bearings, at least one of the bearings including a hybrid-type low-loss bearing.

Assignees

• Gen Electric

Inventors

• Davidson Dwight Eric
• Butkiewicz Jeffrey John
• Delgado Marquez Adolfo
• Van Dam Jeremy Daniel

Classifications

• F02C7/36

  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 title

• F04D29/053

  Shafts · CPC title

• F16C32/0629

  supported by a liquid cushion, e.g. oil cushion · CPC title

• F01D15/12

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F16C2360/23

  Gas turbine engines · CPC title