Donald E Haddad

US Patent:

49999915, Mar 19, 1991

Filed:

Oct 12, 1989

Appl. No.:

7/420199

Inventors:

Donald E. Haddad - Amston CT
Emilio Pereiras - Shelton CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02C 718

US Classification:

60 3902

Abstract:

A method for controlling radial clearance in a gas turbine engine (10) uses a mathematical algorithm to synthesize the current clearance. delta. , including the transient effects of prior engine operations. The synthesized clearance is compared (202) to a schedule of desired clearance (206) for closing. delta. a cooling air modulating valve (44) as required to avoid rubbing between the rotating blade tips and surrounding shroud.

US Patent:

59279427, Jul 27, 1999

Filed:

Oct 27, 1993

Appl. No.:

8/144087

Inventors:

Matthew Stahl - College Station TX
Daniel E. Kane - Tolland CT
James R. Murdock - Tolland CT
Donald E. Haddad - Amston CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 1108

US Classification:

415115

Abstract:

A shroud segment for a gas turbine engine includes a rail engaged with adjacent support structure to retain the segment and to provide sealing between the segment and the adjacent structure. Various construction details are disclosed which provide an effective sealing and retaining feature that permits differing thermal growth between the segment and the support structure. In a particular embodiment, a shroud segment includes a rail along a forward edge. The rail is engaged with a recess in the support structure to retain the segment and with a band which positions the segment and seals the forward edge.

US Patent:

53339924, Aug 2, 1994

Filed:

Feb 5, 1993

Appl. No.:

8/014033

Inventors:

Daniel E. Kane - Tolland CT
Donald E. Haddad - Amston CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 2526

US Classification:

415138

Abstract:

A coolable outer air seal assembly for a gas turbine engine is disclosed. Various construction details are developed which provide an outer air seal assembly comprised of a plurality of seal segments including bumpers adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments. In one particular embodiment, each seal segment includes a mating surface having a plurality of bumpers disposed adjacent to cooling fluid channel outlets and an axially extending ridge disposed along the radially outer edge of the mating surface. The bumpers extend circumferentially a distance H. sub. b to maintain a minimum opening G. sub. min between adjacent seal segments and extend a radial distance W. sub. b to restrict fluid from flowing axially through the clearance gap. The ridge extends radially outward to define in part a seal edge for engaging a feather seal.