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US 2018/0238241 A1Published application
Gear system architecture for gas turbine engine
AssigneeUnited Technologies Corporation
InventorWilliam G. Sheridan
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a gear system that transfers power input from a fan drive turbine to a fan through a gear system with a gear reduction ratio greater than 2.3. A flexible mount supports the gear system and accommodates movement of the gear system relative to an engine static structure. A lubrication system provides lubricant flow to a plurality of rotating components including bearing systems and the gear system and has a maximum capacity for removing thermal energy less than or equal to no more than 2% of power input into the gear system.
Claims30
A gas turbine engine comprising:
- a fan including a plurality of fan blades rotatable about an axis;
- a fan pressure ratio across a fan blade alone of less than 1.45;
- a bypass duct;
- a compressor section;
- a bypass ratio greater than (ten) 10, the bypass ratio being defined as the portion of air delivered into the bypass duct divided by the amount of air delivered into the compressor section;
- a combustor in communication with the compressor section;
- a fan drive turbine in communication with the combustor, the fan drive turbine comprising a pressure ratio greater than about 5, wherein the fan drive turbine further includes an inlet having an inlet pressure, and an outlet that is prior to any exhaust nozzle and having an outlet pressure, and the pressure ratio of the fan drive turbine is a ratio of the inlet pressure to the outlet pressure;
- a gear system providing a speed reduction between the fan drive turbine and the fan and transferring power input from the fan drive turbine to the fan at an efficiency greater than 98%, wherein the gear system further comprises a gear reduction ratio of greater than 2.3;
- a mount flexibly supporting the gear system through the static structure of the engine and accommodating movement between the gear system and the static structure;
- a lubrication system providing lubricant to a plurality of rotating components of the engine, including the gear system, and removing thermal energy from the lubricant;
- and
- a load limiter constraining movement of the gear system during an unbalanced load condition;
- wherein the load limiter constrains radial loads and torsional loads within defined limits.
10 more elements
A gas turbine engine comprising:
- a fan having less than twenty (20) fan blades rotatable about an axis;
- a bypass duct;
- a compressor section;
- a bypass ratio greater than (ten) 10, the bypass ratio being defined as the portion of air delivered into the bypass duct divided by the amount of air delivered into the compressor section;
- a combustor in fluid communication with the compressor section;
- a fan drive turbine in communication with the combustor, the fan drive turbine including a plurality of fan drive turbine rotors, wherein a ratio between the number of fan blades and the number of fan drive turbine rotors is between 3.3 and 8.6;
- a second turbine in communication with the combustor, wherein the second turbine is a two stage turbine;
- a gear system providing a speed reduction between the fan drive turbine and the fan and transfer power input from the fan drive turbine to the fan at an efficiency greater than 99%, wherein the gear system further comprises a gear reduction ratio of greater than 2.3;
- a lubrication system providing lubricant to a plurality of rotating engine components, including at least one bearing assembly and the gear system, and removing thermal energy from the lubricant;
- and
- a load limiter operative to constrain movement of the gear system during an unbalanced load condition.
8 more elements
Dependencies are inferred from the claim text.