Fan case and fan case manufacturing method

Patent metadata

Field	Value
Publication number	US-10280939-B2
Application number	US-201615186641-A
Country	US
Kind code	B2
Filing date	Jun 20, 2016
Priority date	Dec 20, 2013
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A cylindrical case body made of a composite material; a linking ring made of aluminum, fitted and fixed to a rear end portion of the case body and having an annular groove which receives a reverse thrust load from a reverse thrust transmission body; and ring constituent bodies made of titanium alloy, each of which is placed in the rear end portion of the case body and has an arcuate groove which undertakes a reverse thrust load larger than that received by the linking ring, are provided in a fan case. The ring constituent bodies are fitted in notches of the linking ring and are brought into contact with outward receiving walls of the linking ring. The ring constituent bodies are positioned relative to the case body in the axis direction and in the radial direction, and the annular groove and the arcuate grooves continue to each other.

First claim

The invention claimed is:

1. A fan case that covers fan blades of an aircraft jet engine, the fan case comprising:
a case body in a cylindrical shape, the case body being made of a composite material in which reinforcing fibers are impregnated with a thermosetting resin;
a linking ring, the linking ring being made of Al, having an annular groove opened in a centrifugal direction, and being fitted and fixed to an outer peripheral side of a peripheral wall in a rear end portion of the case body, the annular groove being being configured to be used for linking with a reverse thrust transmission body and receiving a first reverse thrust load; and
a ring constituent body, the ring constituent body being made of Ti alloy, having an arcuate groove opened in the centrifugal direction, and being located on the peripheral wall in the rear end portion of the case body, the arcuate groove being configured to be used for linking with the reverse thrust transmission body and undertaking a second reverse thrust load larger than the first reverse thrust load received by the linking ring, wherein
the ring constituent body is fitted in a notch, the notch being formed in the linking ring and being opened toward a rear of the aircraft jet engine, so that the linking ring and the ring constituent body are integrated with each other,
the ring constituent body is positioned relative to the case body in a radial direction and in an axial direction respectively by locating the ring constituent body on the peripheral wall of the case body, and by bringing the ring constituent body into contact with, and fixing the ring constituent body to, an outward receiving wall formed on the linking ring and protruding in the centrifugal direction, and
the annular groove of the linking ring and the arcuate groove of the ring constituent body are continuous with each other.

2. A method of manufacturing a fan case that covers fan blades of an aircraft jet engine, the method comprising:
molding a case body in a cylindrical shape, the case body being made of a composite material in which reinforcing fibers are impregnated with a thermosetting resin;
fitting and fixing a linking ring to an outer peripheral side of a peripheral wall in a rear end portion of the case body, the linking ring being made of Al and having an annular groove opened in a centrifugal direction, the annular groove being configured to be used for linking with a reverse thrust transmission body and receiving a first reverse thrust load;
fitting a ring constituent body into a notch formed in the linking ring and opened toward a rear of the aircraft jet engine, on the peripheral wall in the rear end portion of the case body, and integrating the ring constituent body with the linking ring, the ring constituent body being made of Ti alloy and having an arcuate groove opened in the centrifugal direction, the arcuate groove being configured to be used for linking with the reverse thrust transmission body and undertaking a second reverse thrust load larger than the first reverse thrust load received by the linking ring;
positioning the ring constituent body relative to the case body in a radial direction and in an axial direction respectively, by locating the ring constituent body on the peripheral wall of the case body, and by bringing the ring constituent body into contact with, and fixing the ring constituent body to, an outward receiving wall formed on the linking ring and protruding in the centrifugal direction; and
performing a series of groove finishing to the annular groove of the linking ring and the arcuate groove of the ring constituent body which are allowed to be continuous with each other through each positioning of the ring constituent body relative to the case body in the axial direction and in the radial direction.

Assignees

• Ihi Corp
• Ihi Aerospace Co Ltd

Inventors

• Tanaka Agamu
• Mori Yuji
• Harada Takashi
• Okumura Ikuo
• Ishimoto Kenji

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2300/603

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/82

  Jet pipe walls, e.g. liners · CPC title

• F02K1/64 Primary

  Reversing fan flow · CPC title