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US 2025/0154881 A1Published application
Gas turbine engine front section
AssigneeRtx Corporation
InventorsFrederick M. Schwarz, William G. Sheridan
Life of this patent
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Abstract
A gas turbine engine includes a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades, a compressor section including a first compressor and a second compressor aft of the first compressor relative to an engine longitudinal axis, and a turbine section including a first turbine and a second turbine. A geared architecture that interconnects the first turbine and the propulsor hub such that the fan hub is rotatable at a lower relative speed than the first turbine. A compressor inlet passage is disposed annularly about the geared architecture.
Claims22
A gas turbine engine comprising:
- a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades;
- a compressor section including a first compressor and a second compressor aft of the first compressor relative to an engine longitudinal axis;
- a turbine section including a first turbine and a second turbine, wherein the second turbine drives the second compressor, and the first compressor has a greater number of stages than the second turbine;
- a geared architecture that interconnects the first turbine and the propulsor hub such that the fan hub is rotatable at a lower relative speed than the first turbine, the geared architecture including a gear volume between 1318 in3 and 1977 in3, and the geared architecture including a gear reduction ratio of greater than 2.3, wherein a power transfer parameter is defined as power transferred through the geared architecture divided by the gear volume multiplied by the gear reduction ratio, and the power transfer parameter is between 430 and 645;
- and
- a compressor inlet passage disposed annularly about the geared architecture, the compressor inlet passage establishing a flow path between the propulsor section and the compressor section, the compressor inlet passage including an inlet at a splitter adjacent to the propulsor section and an outlet adjacent to the compressor section.
3 more elements
A gas engine comprising:
- a propulsor section including a propulsor hub supporting a plurality of propulsor blades;
- a geared architecture including an input driven by a first turbine section and an output that rotates the propulsor hub at a lower relative speed than the first turbine;
- and
- a compressor entrance passage disposed around the geared architecture, the compressor entrance passage including an inlet disposed at an inlet diameter and an outlet disposed at an outlet diameter, wherein a ratio of the inlet diameter to the outlet diameter is between 1.10 and 1.64, the geared architecture including an outer diameter that is less than the inlet diameter, and an overall axial length is established between a forward portion of the propulsor hub and a forward bearing assembly that supports a forward portion of a shaft that drives the input of the geared architecture, and a ratio of the overall length to an axial length of the geared architecture is between 4.8 and 16.2.
1 more element
A gas turbine engine comprising:
- a propulsor section including a propulsor hub, the propulsor hub including a hub diameter supporting a plurality of propulsor blades including a tip diameter, a ratio of the hub diameter to the tip diameter being between 0.24 and 0.36;
- a geared architecture including an input driven by a first turbine for rotating the propulsor at a lower relative speed than the first turbine, wherein a ratio between the number of the propulsor blades and the number of turbine rotors of the first turbine is between 3.3 and 8.6;
- and
- a transitional entrance passage arranged to communicate flow between the propulsor section and a compressor section, the compressor section including a first compressor having a plurality of stages, the transitional entrance passage including an inlet disposed at an inlet diameter and an outlet to the compressor section disposed at an outlet diameter, the geared architecture including an outer diameter that is less than the inlet diameter of the transitional entrance passage, the outlet adjacent to the first compressor, and a ratio of the hub diameter to the inlet diameter being between 0.70 and 0.90;
- wherein the outlet is axially forward of a forwardmost stage of the compressor section relative to an engine longitudinal axis, the first compressor comprises the forwardmost stage, and a ratio of the inlet diameter to the outlet diameter is between 1.10 and 1.64.
2 more elements
Dependencies are inferred from the claim text.