# US 5,350,557 A · Impermeable, abradable seal and method for the production thereof

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- Number: US 5,350,557 A
- Document ID: US5350557A
- Status: Granted
- Kind: A
- Application number: 07/764,204
- Filed: 1991-09-23
- Granted: 1994-09-27
- Earliest claimed: 1991-09-23
- Assignees: Technetics Corporation
- Inventors: Gregory P. Jarrabet; Lixion Lu
- Web page: https://patentgrep.com/patent/US5350557A

## CPC

- B22F 3/26: Impregnating {(making ferrous alloys by impregnation C22C33/0242)}
- F01D 11/12: using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- 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)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

Gas turbine engines employ a variety of abradable liners to decrease the clearance between the rotating components and the surrounding casing. There is normally a trade-off between porosity, (and concomitant permeability) and the abradability of the liner material, such that materials with good abradability are permeable to gas flow--resulting in performance losses. Permeability of porous liners is decreased by infiltrating the liner with a low-viscosity liquid containing a metal or metal oxide. After infiltration, the viscosity of the liquid is substantially increased to prevent its egress from the porous liner. Thereafter, the liner is heated at an elevated temperature to drive off the remaining liquid and provide an oxide which blocks the passages and decreases the permeability of the liner.

## Claims

### Claim 1

In the production of an abradable liner material, comprising a rigid, skeleton-like matrix, the pores of which are at least partially filled with a metal or metal compound, to substantially decrease the permeability of the liner under the high temperature applications encountered in such turbomachinery, the improvement which comprises,
infiltrating the pores of said matrix to a depth beyond the surface regions of the liner with a solution or dispersion containing an effective quantity of at least one metal in elementary or combined form, said solution or dispersion having a viscosity low enough to adequately penetrate the pores of the matrix, the quantity of said metal being sufficient, such that upon heating, the gas permeability of the liner will be less than 50% of the unfilled matrix,
preventing the egress of the infiltrate from the matrix,
heating the infiltrated matrix under conditions which cause the infiltrate to form, and form a derivative which: (i) is stable at such high temperatures and (ii) adheres to the matrix material, such that it fills the pores thereof to a degree sufficient to achieve said decrease in the gas permeability of the liner.

### Claim 2 (depends on 1)

The method of claim 1, wherein the egress of the infiltrate is prevented by drying the infiltrated matrix at a temperature and pressure sufficient to drive off a major portion of the solvent.

### Claim 3 (depends on 2)

The method of claim 2, wherein said drying is conducted to convert said infiltrate into a substance capable of foaming when rapidly heated to an elevated temperature.

### Claim 4 (depends on 3)

The method of claim 3, wherein said heating is sufficiently rapid to convert the substance into microspheres or closed cells which fill the pores of said structure.

### Claim 5 (depends on 4)

The method of claim 4, wherein a majority of said pores have an effective diameter below 40 microns.

### Claim 6 (depends on 4)

The method of claim 4, wherein said infiltrate is an aqueous solution of chromic acid.