Paired blade assembly

• US 4,098,559 A
• Filed: 07/26/1976
• Issued: 07/04/1978
• Est. Priority Date: 07/26/1976
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Price, Jerry Lee
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/708,680
• Time in Patent Office: 708 Days
• Field of Search: 416/218, 416/230, 416/229, 416/229 A, 416/241 A, 416/212, 416/212 A, 416/248
• US Class Current: 416/230
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/3053 by means of pins
• CPC Class Codes: F01D 5/3069 between two discs or rings
• CPC Class Codes: F01D 5/34 Rotor-blade aggregates of unitary construction , e.g. formed of sheet laminae; discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/614 Fibres or filaments

Abstract

A rotor blade system which is adaptd for long term reliable operation in a gas turbine engine is disclosed. Techniques incorporating composite materials into the rotor system are developed. One rotor structure shown utilizes a paired blade assembly having a core of continuous fibers running from the tip of one blade to the tip of the adjacent blade. Each of said paired blade assemblies is mchanically detachable from the engine rotor.

Claims

1. A rotor assembly for a gas turbine engine, which comprises:

a rotor disk having a front plate and a rear plate which are contoured to form an outwardly facing circumferentially extending channel therebetween; and

a plurality of unitized blade assemblies mounted in and extending outwardly from said channel, each assembly including

a central platform block adapted for mechanical attachment to the rotor disk,

a core of continuous fibers having a central portion which extends around said platform block, and having a first end and an opposite end which extend outwardly from said block in essentially the same direction;

an outer platform block adapted to hold, in cooperation with the central platform block, the central portion of the core of continuous fibers therebetween;

a first shell having an airfoil-shaped contour which encases said first end of the core of continuous fibers to form a first rotor blade; and

a second shell having an airfoil-shaped contour which engages said opposite end of the core of continuous fibers to form a second rotor blade.

2. The invention according to claim 1 which further includes a reinforcing ring of continuous fibers extending circumferentially about the rotor disk of said assembly and adapted to carry a substantial portion of the centrifugally generated hoop stresses imparted to the disk by the blades of the assembly during rotation.