# US 5,705,280 A · Composite materials and methods of manufacture and use

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- Number: US 5,705,280 A
- Document ID: US5705280A
- Status: Granted
- Kind: A
- Application number: 08/772,234
- Filed: 1996-12-23
- Granted: 1998-01-06
- Earliest claimed: 1994-11-29
- Inventors: Herbert W. Doty
- Web page: https://patentgrep.com/patent/US5705280A

## CPC

- C22C 32/0026: {Matrix based on Ni, Co, Cr or alloys thereof}
- B22F 3/23: involving a self-propagating high-temperature synthesis or reaction sintering step {(making cermets by reaction sintering C22C1/051)}
- F01D 5/28: Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion
- F05C 2201/0466: Nickel
- F05D 2300/173: Aluminium alloys, e.g. AlCuMgPb
- F05D 2300/603: Composites; e.g. fibre-reinforced
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- Y10T 428/12056: Entirely inorganic
- C22C: ALLOYS (treatment of alloys C21D, C22F)
- B22F: WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER (making alloys by powder metallurgy C22C); APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05C: INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

This invention relates to composite materials and the production of composite materials that are designed for use under high stress and at high temperatures. More particularly, this invention relates to materials suited for use in turbine engines, such as those used in aircraft, that must withstand high temperature, high stress, corrosion and oxidation. The invention specifically relates to composite materials which have alloy matrices, e.g., nickel aluminide, reinforced with a substantially continuous, interpenetrating, and interconnected network of a metal oxide. These composite materials have superior properties as compared to superalloys, intermetallics, ceramics, or artificially reinforced materials.

## Claims

### Claim 1

A composite material consisting essentially of a NiAl matrix, and an in situ Al.sub.2 O.sub.3 reinforcement network, wherein said matrix and reinforcement are substantially continuous, interconnecting, interpenetrating, and interfacially bonded.

### Claim 2

A composite material consisting essentially of a NiAl matrix, and an in situ Al.sub.2 O.sub.3 reinforcement network, wherein said matrix and reinforcement are substantially continuous, interconnecting, interpenetrating, and interfacially bonded, wherein said composite is water quenched and has a fracture toughness of at least 16 MPa.sqroot.m.