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US 10,294,965 B2Granted
Compression system for a turbine engine
AssigneeHoneywell International Inc.
InventorsNick Nolcheff, Michael LaMar Trego, John Repp, James Kroeger
Life of this patent
Estimating the term…
Abstract
A blisk fan is provided for a turbine engine propulsion system. The blisk fan includes a hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades extending radially outward from the hub to define a fan leading edge tip diameter. Each of the blades has a first vibratory mode at a natural frequency, which is greater than a first fan order and less than a second fan order at the maximum rotational speed. The compression system preferably has a balance factor of the compression system between 1.9 and 3.2.
Claims20
A compression system for a turbine engine propulsion system comprising:
- an axi-centrifugal compressor including an axial compressor section having a compressor inlet and a centrifugal compressor section having a compressor outlet;
- a blisk fan positioned upstream of the axi-centrifugal compressor for directing at least a portion of a pressurized fluid stream to the compressor inlet, the blisk fan having a rotor hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades materially joined with the rotor hub and extending radially outward from the rotor hub to define a fan leading edge tip diameter, wherein each of the plurality of blades has a first vibratory mode at a natural frequency which is greater than a first fan order and less than a second fan order at the maximum rotational speed;
- and
- wherein a balance factor of the compression system is between 1.9 and 3.2.
1 more element
A propulsion system, comprising:
- a turbine engine disposed in an engine cowl and operably coupled to a shaft assembly for rotation about a rotational axis, the turbine engine having an axi-centrifugal compressor including an axial compressor section having a compressor inlet and a centrifugal compressor section having a compressor outlet;
- a fan section disposed in the engine cowl upstream of the axi-centrifugal compressor and operably coupled to the shaft assembly for drawing a fluid into the engine cowl and directing at least a portion of a pressurized fluid stream into the compressor inlet, the fan section including a rotor hub configured to rotate about the rotational axis at a maximum rotational speed, and a plurality of blades materially joined with the rotor hub and extending radially outward from the rotor hub to define a fan leading edge tip diameter, wherein each of the plurality of blades has a first vibratory mode at a natural frequency which is greater than a first fan order and less than a second fan order at the maximum rotational speed;
- and
- wherein a balance factor of the fan section and axi-centrifugal compressor is between 1.9 and 3.2.
1 more element
A propulsion system, comprising:
- a turbine engine disposed in an engine cowl and operably coupled to a shaft assembly for rotation about a rotational axis, the turbine engine having an axi-centrifugal compressor including an axial compressor section having a compressor inlet and a centrifugal compressor section having a compressor outlet;
- and
- a fan section disposed in the engine cowl upstream of the axi-centrifugal compressor and operably coupled to the shaft assembly for drawing a fluid into the engine cowl and directing at least a portion of a pressurized fluid stream into the compressor inlet, the fan section including a rotor hub configured to rotate about the rotational axis at a maximum rotational speed and having an annular portion, and a plurality of blades materially joined to the rotor hub, each blade intersecting the annular portion of the rotor hub at a proximal end to define an airflow surface having a hub slope that is not less than 20 degrees with respect to the rotational axis and extending radially from an inner root to an outer tip at a distal end to define a fan leading edge tip diameter, each blade extending axially from a leading edge to a trailing edge to define an airfoil having an aspect ratio not less than 1.2;
- wherein each blade has a first vibratory mode at a natural frequency which is greater than a first fan order and less than a second fan order at the maximum rotational speed;
- and
- wherein a balance factor of the fan section and axi-centrifugal compressor is between 1.9 and 3.2.
3 more elements
Dependencies are inferred from the claim text.