Geared turbofan engine with targeted modular efficiency
AssigneeRaytheon Technologies Corporation
InventorFrederick M. Schwarz
Life of this patent
Estimating the term…
Abstract
A turbofan engine includes a fan section including a fan blade having a leading edge and hub to tip ratio of less than about 0.34 and greater than about 0.020 measured at the leading edge and a speed change mechanism with gear ratio greater than about 2.6 to 1. A first compression section includes a last blade trailing edge radial tip length that is greater than about 67% of the radial tip length of a leading edge of a first stage of the first compression section. A second compression section includes a last blade trailing edge radial tip length that is greater than about 57% of a radial tip length of a leading edge of a first stage of the first compression section.
Claims30
A turbofan engine comprising;
- a fan section including a fan blade having a leading edge and a hub to tip ratio of less than 0.34 and greater than 0.020 measured at the leading edge;
- a first compression section;
- a second compression section including a last blade trailing edge radial tip length that is greater than 57% of the radial tip length of the leading edge of the first stage of the second compression section;
- a turbine section including a fan drive turbine section and at least two turbine stages forward of a first turbine blade of the fan drive turbine section;
- and
- a mid-turbine frame disposed between the fan drive turbine and the at least two turbine stages for guiding core flow into the fan drive turbine, the mid-turbine frame supporting a bearing system for one of the fan drive turbine and the at least two turbine stages.
A turbofan engine comprising:
- a fan section providing a bypass ratio greater than 8, the fan section includes a plurality of fan blades supported on a hub;
- a speed change system coupled to the hub with a gear ratio greater than about 2.6 to 1;
- a first compression section including a last blade trailing edge tip length that is greater than 67% of the radial length of a first stage leading edge of the first compression section, wherein the first compression section operates at an efficiency of at least 0.84;
- a turbine section including a fan drive turbine section coupled to the speed change system and at least two turbine stages forward of a first turbine blade of the fan drive turbine section;
- and
- a mid-turbine frame disposed between the fan drive turbine and the at least two turbine stages for guiding core flow into the fan drive turbine, the mid-turbine frame supporting a bearing system for one of the fan drive turbine and the at least two turbine stages.
A turbofan engine comprising:
- a fan section providing a bypass ratio greater than 8, the fan section includes a plurality of fan blades supported on a hub, wherein at least one of the plurality of fan blades includes a leading edge and a hub to tip ratio is less than about 0.34 and greater than about 0.020 measured at the leading edge;
- a three-stage first compression section disposed aft of the speed change system, the three-stage first compression section including a first rotating compressor blade with a leading edge and a last rotating compressor blade with a trailing edge, wherein a radial distance from an engine longitudinal axis to a tip of the trailing edge of the last rotating compressor blade is greater than 67% of a radial distance from the engine longitudinal axis to a tip of the first rotating compressor blade at the leading edge;
- an eight stage second compression section including a last rotating compressor blade with a trailing edge tip that includes a radial length that is greater than 57% of a radial length of the first rotating compressor blade at the leading edge of the eight-stage first compression section;
- a turbine section including a fan drive turbine section and a two stage turbine section forward of a first turbine blade of the fan drive turbine section;
- and
- a geared architecture coupled between the fan drive turbine and the hub of the fan section, the geared architecture including with a gear ratio greater than about 2.6 to 1.
Dependencies are inferred from the claim text.