Fan rotor blade of aircraft jet engine

Patent metadata

Field	Value
Publication number	US-9702257-B2
Application number	US-201414444585-A
Country	US
Kind code	B2
Filing date	Jul 28, 2014
Priority date	Jan 30, 2012
Publication date	Jul 11, 2017
Grant date	Jul 11, 2017

Abstract

A fan rotor blade includes a blade body made from a composite material of a resin and fibers, and having a pressure surface facing one side in a rotation direction and a suction surface facing the other side in the rotation direction. The blade body is provided with a sheath which 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, which is located on an upstream side in the direction of intake of external air, and the vicinity thereof. A tip end portion of the sheath extends from the leading edge portion side of the blade body to a trailing edge portion side of the blade body. An end portion of the tip end portion of the sheath is flush with the trailing edge portion of the blade body.

First claim

What is claimed is:

1. A fan rotor blade for an aircraft jet engine comprising:
a blade body made from a composite material of a resin and reinforcing fibers, including: a pressure surface and a suction surface both oppositely facing in a thickness direction of the blade body, a leading edge portion located on an upstream end of the blade body, a trailing edge portion located on a downstream end of the blade body, being at least a part of a trailing edge of the fan rotor blade, a tip end in a longitudinal direction, and a base end in a longitudinal direction being held by the fan disk; and
a sheath being more rigid than the blade body, extending in the longitudinal direction of the blade body and fixed to the blade body to cover the leading edge portion of the blade body and the vicinity thereof,
wherein the sheath includes a tip end portion integrally formed therewith extending from the leading edge portion of the blade body toward the trailing edge portion of the blade body to cover the tip end of the blade body and terminated with a downstream end portion of the tip end portion, and
the downstream end portion of the tip end portion of the sheath is located at a position within 20% from the trailing edge in a range from the leading edge portion to the trailing edge portion, or projects downstream from the trailing edge portion of the blade body.

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

3. The fan rotor blade for an aircraft jet engine according to claim 1 , wherein the downstream end portion of the sheath is located closer to a leading edge side of the fan rotor blade than the trailing edge portion of the blade body.

4. The fan rotor blade for an aircraft jet engine according to claim 1 , wherein the downstream end portion of the sheath is flush with the trailing edge portion of the blade body.

Assignees

• Ihi Corp

Inventors

• Yagi Hiroyuki
• Kuroki Hiroshi
• Obuchi Kenro

Classifications

• 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

• F05D2240/303

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

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F02K3/06

  with front fan · CPC title

• F04D29/324

  Blades · CPC title