Anti-windmilling system for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorGary D. Roberge
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a compressor having a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine has a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. A low speed accessory gearbox is interfaced with the first shaft via a mechanical interface. The low speed accessory gearbox includes a mechanical brake.
Claims17
A gas turbine engine comprising:
- a compressor having a first compressor section and a second compressor section;
- a combustor fluidly connected to the compressor;
- a turbine fluidly connected to the combustor, the turbine having a first turbine section and a second turbine section;
- a first shaft connecting the first compressor section and the first turbine section;
- a second shaft connecting the second compressor section and the second turbine section;
- a fan connected to said first shaft via a geared architecture;
- a low speed accessory gearbox interfaced with the first shaft via a mechanical interface, and interfaced with at least one engine system other than the first shaft, the low speed accessory gearbox being configured to provide rotational power to the at least one engine system;
- and
- the low speed accessory gearbox including a mechanical brake.
A gas turbine engine comprising:
- a compressor having a first compressor section and a second compressor section;
- a combustor fluidly connected to the compressor;
- a turbine fluidly connected to the combustor, the turbine having a first turbine section and a second turbine section;
- a first shaft connecting the first compressor section and the first turbine section;
- a second shaft connecting the second compressor section and the second turbine section;
- a fan connected to said first shaft via a first geared architecture;
- and
- a brake interfaced with the first shaft via at least a second geared architecture, wherein the brake is integrated into an accessory gearbox connected to said first shaft and the accessory gearbox is interfaced with at least one engine system other than the first shaft, the accessory gearbox being configured to provide rotational power to the at least one engine system.
A method for preventing rotation of a shaft in a gas turbine engine comprising:
- preventing rotation of a gear system within a low speed accessory gearbox via application of a brake, wherein the low speed accessory gearbox is interfaced with at least one engine system other than a low speed engine shaft, is interfaced with the low speed engine shaft, and is configured to provide rotational power to the at least one engine system;
- and
- preventing rotation of a fan drive gear system when said brake is applied via a mechanical interface between said low speed accessory gearbox and said fan drive gear system.
Dependencies are inferred from the claim text.