Robert H Zipps

58367446, Nov 17, 1998

Apr 24, 1997

8/839997

Robert H. Zipps - East Hartford CT
Reginald H. Spaulding - Hebron CT
Edward S. Todd - East Hampton CT
Robert F. Kasprow - Wethersfield CT
Herman C. Klapproth - Enfield CT
Douglas A. Welch - Portland CT
Phyllis L. Kurz - Hebron CT
Joseph J. Cafasso - Glastonbury CT

United Technologies Corporation - Hartford CT

F04D 2938

416193A

The present invention relates to a fan blade in an axial gas turbine engine. The blade platform is constructed to fracture adjacent the airfoil portion of the blade so as to locate the fractured edge of the platform in the root portion. As a result of this benign platform, damage to successive fan blades during a blade loss condition is reduced. In addition, various construction details are developed in the airfoil and root portion of the fan blade to reduce damage to fan blades during impact with adjacent blades.

61460990, Nov 14, 2000

Jul 30, 1998

9/127710

Robert H. Zipps - East Hartford CT
Reginald H. Spaulding - Hebron CT
Edward S. Todd - East Hampton CT
Robert F. Kasprow - Wethersfield CT
Herman C. Klapproth - Enfield CT
Douglas A. Welch - Portland CT
Phyllis L. Kurz - Hebron CT
Joseph J. Cafasso - Glastonbury CT

United Technologies Corporation - Hartford CT

F04D 2938

416193A

A fan in an axial flow gas turbine engine includes a plurality of fan blades. Each fan blade includes an airfoil portion and a root portion with a platform disposed radially therebetween. The platform of each blade extends circumferentially from the blade and is dimensioned to define, with an adjacent platform, an enlarged gap to insure that contact between adjacent platforms is avoided when a blade is released during a blade loss condition. A seal is provided to seal the enlarged gap between adjacent platforms during normal operation of the gas turbine engine.

46219790, Nov 11, 1986

Nov 30, 1979

6/099058

Robert H. Zipps - East Hartford CT
Chester H. Rynaski - Meriden CT
Graham B. Fulton - Manchester CT

United Technologies Corporation - Hartford CT

F01D 530

416219R

The present invention provides improvements to fan rotor blades of turbofan gas turbine engines. Increased low cycle fatigue life is sought, and a specific object is to obtain a more nearly uniform chordwise distribution of maximum stress levels across the root sections of fan blades. In one effective embodiment incorporating concepts of the present invention the root section of a fan blade is contoured to an arcuate geometry which approximates the contour of the airfoil cross section at the inner wall of the working medium flowpath. Further contour specifications for reducing local stress levels are discussed.

47985194, Jan 17, 1989

Aug 24, 1987

7/088776

Robert H. Zipps - East Hartford CT
Kent A. Lyons - East Haddam CT
Evans E. Griffin - Colchester CT

United Technologies Corporation - Hartford CT

F01D 522

416191

A compressor blade assembly for a compressor operating at transonic or supersonic blade speeds has a part span shroud. The shroud is twisted having a first angle in the direction of airflow on one side of the shock wave and a second angle in the direction of airflow on the other side of the shock wave.