Fan rotor blade and fan

Patent metadata

Field	Value
Publication number	US-9359064-B2
Application number	US-201113997834-A
Country	US
Kind code	B2
Filing date	Dec 16, 2011
Priority date	Dec 28, 2010
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

A fan rotor blade has a rotor blade leading edge. On a hub side of the rotor blade leading edge, a vertical hub section is formed. From a top end of the vertical hub section to a mid-span side of the rotor blade leading edge, a backward tilt mid-span section is formed. From a top end of the backward tilt mid-span section to a tip end of the rotor blade leading edge, a forward tilt tip section is formed. From a hub end of the rotor blade leading edge to a base end of the vertical hub section, a backward tilt hub section is formed. The backward tilt hub section is backwardly tilted so that a top end thereof is positioned behind a base end thereof.

First claim

The invention claimed is:

1. A fan rotor blade used for a fan that takes air into an annular core flow path formed inside an engine case of an aircraft engine and an annular bypass flow path formed inside the engine case concentrically with and outside the core flow path, the fan rotor blade comprising:
a rotor blade leading edge that includes:
a vertical hub section formed on a hub side and substantially normal to an axial center of the fan;
a backward tilt mid-span section formed from a top end of the vertical hub section to a mid-span side and backwardly tilted so that a top end thereof is positioned behind a base end thereof;
a forward tilt tip section formed from the top end of the backward tilt mid-span section to a tip side and forwardly tilted so that a top end thereof is positioned ahead of a base end thereof; and
a backward tilt hub section formed from a hub end of the rotor blade leading edge to a base end of the vertical hub section and backwardly tilted so that a top end thereof is positioned behind a base end thereof,

wherein an absolute value of a backward tilt angle of the backward tilt hub section becomes maximum at the base end thereof, gradually decreases toward the vertical hub section, and is smoothly connected to the vertical hub section having a sweep angle of substantially zero degrees, the backward tilt angle having a negative sweep angle throughout the backward tilt hub section between the base end of the backward tilt hub section and the top end of the backward tilt hub section.

2. The fan rotor blade according to claim 1 , wherein:
a first span length from the hub end of the rotor blade leading edge to the top end of the vertical hub section is set to be 20 to 50% of a total span length of the rotor blade leading edge;
a second span length from the hub end of the rotor blade leading edge to the top end of the backward tilt hub section is set to be 5 to 25% of the total span length of the rotor blade leading edge; and
a maximum absolute value of the backward tilt angle of the backward tilt hub section is set to be 5 to 45 degrees.

3. The fan rotor blade according to claim 1 , wherein:
a third span length from the hub end of the rotor blade leading edge to the base end of the forward tilt tip section is set to be 60 to 90% of the total span length of the rotor blade leading edge; and
a maximum absolute value of a forward tilt angle of the forward tilt tip section is set to be 5 to 45 degrees.

4. The fan rotor blade according to claim 1 , comprising:
a blade body made of a composite material of thermosetting resin or thermoplastic resin and reinforcement fiber;
a blade root formed integral with a base end side of the blade body and made of a composite material of thermosetting resin or thermoplastic resin and reinforcement fiber; and
a sheath arranged on a front edge side of the blade body, made of metal, and protecting the front edge side of the blade body, the front edge of the sheath being the rotor blade leading edge.

5. A fan taking air into an annular core flow path formed inside an engine case of an aircraft engine and a bypass flow path formed inside the engine case concentrically with and outside the core flow path, comprising:
a fan disk being rotatable, arranged around an axial center in the engine case, and provided with a plurality of fitting grooves on an outer circumferential face thereof at regular intervals in a circumferential direction; and
the fan rotor blade according to claim 1 fitted into each of the fitting grooves of the fan disk.

6. The fan rotor blade according to claim 1 , wherein:
a maximum absolute value of an angle of the vertical hub section is less than a maximum absolute value of a backward tilt angle of the backward tilt mid-span section, and
the maximum absolute value of the angle of the vertical hub section is less than a maximum absolute value of a forward tilt angle of the forward tilt tip section.

Assignees

• Murooka Takeshi
• Ihi Corp

Inventors

• Murooka Takeshi

Classifications

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F04D29/324

  Blades · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• B64C11/00 Primary

  Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft · CPC title