Fan rotor blade of aircraft jet engine

Patent metadata

Field	Value
Publication number	US-10066490-B2
Application number	US-201414444541-A
Country	US
Kind code	B2
Filing date	Jul 28, 2014
Priority date	Jan 30, 2012
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

A fan rotor blade includes a blade body made from a composite material of a resin and fibers, and having a pressure surface and a suction surface. A dovetail capable of being fitted into a fitting groove in a fan disk is provided in a base end of the blade body. The blade body is provided with a sheath. The sheath is more rigid than the blade body and is fixed to the blade body in a state where the sheath covers a leading edge portion of the blade body and the vicinity thereof. The sheath extends in the longitudinal direction of the blade body from a blade root side to a tip end side of the blade body, and a base end portion of the sheath located on the blade root side of the blade body extends to the dovetail.

First claim

What is claimed is:

1. A fan rotor blade for an aircraft jet engine configured to be fitted in a fitting groove formed in a fan disk, and to take external air into a passage formed in an engine case by rotating integrally with the fan disk, the fan rotor blade comprising:
a blade body made from a composite material of a resin and fibers, and including a pressure surface facing one side in a rotation direction and a suction surface facing the other side in the rotation direction;
a fitting portion provided as part of the blade body on one end side of the blade body in a longitudinal direction thereof, the fitting portion being thicker than a remaining region of the blade body and fitted into the fitting groove in the fan disk; and
a sheath being more rigid than the blade body, and fixed to the blade body in a state where the sheath covers a leading edge portion of the blade body and the vicinity thereof, the leading edge portion being located on an upstream side in a direction of intake of the external air; wherein
the sheath extends in the longitudinal direction of the blade body from the one end side to the other end side of the blade body in the longitudinal direction,
a base end portion of the sheath, which is one end of the sheath in the longitudinal direction, is located closer to the one end side of the blade body than the passage formed in the engine case,
the base end portion of the sheath extends to the fitting portion of the blade body and covers part of the fitting portion, the part including a leading end of the fitting portion,
the base end portion is fitted into the fitting groove together with the fitting portion,
the base end portion protrudes less than all other portions of the sheath toward the upstream side in the direction of intake of the external air.

2. The fan rotor blade for an aircraft jet engine according to claim 1 , wherein the base end portion of the sheath is fitted into the fitting groove in the fan disk together with the blade body.

3. The fan rotor blade for an aircraft jet engine according to claim 2 , wherein the sheath is made from a metal material.

4. The fan rotor blade for an aircraft jet engine according to claim 1 , wherein the sheath is made from a metal material.

5. The fan rotor blade for an aircraft engine according to claim 1 , wherein the sheath includes a tip end portion covering a tip end portion of the blade body from a leading edge of the blade body to the trailing edge of the blade body.

6. The fan rotor blade for an aircraft jet engine according to claim 5 , wherein the tip end portion of the sheath body is flush with the trailing edge of the blade body.

7. The fan rotor blade for an aircraft jet engine according to claim 5 , wherein the tip end portion of the sheath body is projected downstream from the trailing edge of the blade body.

8. The fan rotor blade for an aircraft jet engine according to claim 5 , wherein the tip end portion of the sheath body is flush with the trailing edge of the blade body, and
wherein the base end portion of the sheath is fitted into the fitting groove in the fan disk together with the blade body.

9. The fan rotor blade for an aircraft jet engine according to claim 5 , wherein the tip end portion of the sheath body is projected downstream from the trailing edge of the blade body, and
wherein the base end portion of the sheath is fitted into the fitting groove in the fan disk together with the blade body.

10. The fan rotor blade for an aircraft jet engine according to claim 1 , wherein the fitting portion includes a dovetail and the base end portion of the sheath extends to and covers a leading edge of the dovetail.

Assignees

• Ihi Corp

Inventors

• Yagi Hiroyuki
• Kuroki Hiroshi
• Obuchi Kenro

Classifications

• F01D5/147 Primary

  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

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2300/10

  Metals, alloys or intermetallic compounds · CPC title

• F04D29/388

  characterised by construction · CPC title

• F05D2240/303

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