Francis L Detolla

US Patent:

40059464, Feb 1, 1977

Filed:

Jun 20, 1975

Appl. No.:

5/588916

Inventors:

Bertrand Hirsch Brown - Glastonbury CT
Francis Louis DeTolla - Vernon CT
Dale Robert Reilly - Marlborough CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 2524

US Classification:

415136

Abstract:

Methods and apparatus for controlling the radial clearance between the rotor and stator elements in the turbine section of a gas turbine engine is disclosed. A cooling air valve is operatively disposed at the upstream end of the turbine section to control the admission of cooling air to the turbine in response to engine operating temperatures. In one specific embodiment the thermal growth of the case and the stator elements supported thereby is controlled by the valve. At low power conditions the case and the supported elements grow radially with the rotor in response to increasing gas path temperatures. At elevated conditions cooling air is flowable to the case to retard the thermal growth of the case and allow the rotor to grow radially toward the stator elements.

US Patent:

42472482, Jan 27, 1981

Filed:

Dec 20, 1978

Appl. No.:

5/971289

Inventors:

Gary F. Chaplin - Vernon CT
Francis L. DeTolla - Vernon CT
James G. Griffin - West Hartford CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 2528

US Classification:

415136

Abstract:

A support structure for an outer air seal of a gas turbine engine is disclosed. Various construction details which improve the sealing effectiveness of the outer air seal are developed. The outer air seal is held in close proximity to the rotor blades by the circumferentially adjacent support segments.

US Patent:

39921263, Nov 16, 1976

Filed:

Mar 25, 1975

Appl. No.:

5/561712

Inventors:

Henry B. Brown - Manchester CT
Eugene Cantor - Glastonbury CT
Francis L. DeTolla - Vernon CT
Gary J. Vollinger - Simsbury CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

415115

Abstract:

Apparatus for cooling the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the turbine case and extends radially inward across the path of working medium gases flowing through the turbine. A ring which is deformable in response to pressure forces is disposed between the vanes and the turbine case forming an annular chamber from which air is metered to the vanes during operation of the engine for cooling. In one embodiment platform cavities and airfoil cavities are alternately disposed between the vanes and the ring to isolate airfoil cooling air from platform cooling air.

US Patent:

43147933, Feb 9, 1982

Filed:

Dec 20, 1978

Appl. No.:

5/971290

Inventors:

Francis L. DeTolla - Vernon CT
Gary F. Chaplin - Vernon CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 1100
F01D 904

US Classification:

415135

Abstract:

A seal member for a gas turbine engine is disclosed. Various construction details which ensure an adequate fatigue life and increase the sealing effectiveness of the member during engine operation are developed. A metal diaphragm extends from a nonrotating structure inwardly of the engine flow path to engage the stator vanes at engine operating temperature.

US Patent:

39751120, Aug 17, 1976

Filed:

Jun 9, 1975

Appl. No.:

5/585283

Inventors:

Henry Bispham Brown - Manchester CT
Francis Louis DeTolla - Vernon CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 514

US Classification:

415116

Abstract:

Apparatus forming a portion of the outer wall of the flow path for working medium gases in the turbine section of a gas turbine engine is disclosed. The vanes of each turbine stage are grouped into a plurality of vane clusters which are circumferentially disposed in adjacent relationship about the flow path. A shroud which surrounds the tips of the rotor blades immediately upstream of the vane clusters is segmented in integral ratio to the number of vane clusters. The gap between each pair of adjacent vane clusters is circumferentially positioned in axial alignment with one of the gaps between adjacent shroud segments.

US Patent:

51882922, Feb 23, 1993

Filed:

Jun 28, 1991

Appl. No.:

7/724309

Inventors:

Luther R. Frey - Peck KS
Francis L. DeTolla - Jupiter FL

Assignee:

The United States of America as represented by the Secretary of the Air
Force - Washington DC

International Classification:

F02K 112
B64C 1502
B64D 3304

US Classification:

2391273

Abstract:

In a gas turbine engine, in a wall aperture of a 2-D variable area gas turbine exhaust nozzle, at least two members are rotatably and concentrically mounted in such aperture, substantially flush with the wall and in the path of hot exhaust gases flowing thereover, wherein an improvement is provided such that a) a heat shield is mounted on the wall downstream of the two concentric members b) a second liner is mounted on the inner concentric member and spaced thereabove and extends downstream over the outer concentric member, which is recessed relative to the second liner, which liner then overlaps the first liner, c) a third liner is mounted on the wall, upstream of the concentric members and spaced thereabove and extends downstream over the outer concentric member (to effectively submerge same) and overlaps the second liner, the liners being mounted in shingle-style overlap over the members including over the recessed outer concentric member, to thermally shield same. The liners are also elevated relative to the underlying wall and concentric members to provide a passage for cooling air therebetween.