Lawrence T Halstead

US Patent:

48612294, Aug 29, 1989

Filed:

Nov 16, 1987

Appl. No.:

7/120968

Inventors:

Lawrence T. Halstead - Milford MI

Assignee:

Williams International Corporation - Walled Lake MI

International Classification:

F01D 904

US Classification:

415138

Abstract:

A nozzle assembly for a turbine engine comprises an annular ceramic-matrix composite hub having integral radially outwardly extending vanes, and a pair of annular ceramic-matrix composite shrouds which interlockingly engage and secure the radially outermost ends of the vanes, whereby the hub is peripherally supported. The quasi-isotropic laminate structure of both hub and shroud materials generates like physical properties radially and circumferentially in the hub, and axially and circumferentially in the shrouds. Such quasi-isotropism in turn provides cooperative thermal expansion of the hub and shrouds during engine operation, whereby the radial, axial, and circumferential abutting surfaces of the ends of the vanes increasingly interlockingly engage with the correspondingly opposed surfaces of the shrouds to effect increased structural integrity of the nozzle assembly. The nozzle assembly is supported relative to the metallic engine mount therefor by a plurality of axially extending support beams circumferentially spaced about, and secured to, the periphery of the shrouds. The support beams accommodate the disparate radial thermal expansion between the ceramic and metallic components of the engine.

US Patent:

52057097, Apr 27, 1993

Filed:

Mar 24, 1992

Appl. No.:

7/856569

Inventors:

William P. Schimmel - Milford MI
Irvin J. Pollock - Farmington Hills MI
Lawrence T. Halstead - Hartland MI

Assignee:

Williams International Corporation - Walled Lake MI

International Classification:

T04D 2904

US Classification:

4152161

Abstract:

A drum compressor rotor (10) for use in a gas turbine engine comprises a plurality of high strength, low density filaments (18a-d) which are covered with a high temperature adhesive resin and tightly wound around the hub (12) between rows of fan blades (14). The filaments allow an increase in the maximum compressor rotor operating speed thereby increasing the potential performance of the turbine engine. The filament windings (18a-d) are significantly lighter and less expensive than conventional welded metal support disks (106a-c).