Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Jordan J Franklin

Michael A Weisse

Linda S Li

Lee Drozdenko

David R Lyders

Xuedong Zhou

Peter Karkos

Matthew R Zsunkan

Chong H Park

Mouhamadou Diop

Mahesh Gajanan Kavimandan

Daniel W Yebo

Chaitanya Mokkapati

Satyannarayana Chintapalli

Joshua W Sampsell

Sai Deepika Vemula

Vishnu Murthy Pendum

Naveen Prasad Babu Ramireddy Gari

Naga Pradeep Buddhavarapu

A fan blade platform seal includes a platform portion including a first side and a second side opposite the first side. The platform portion further includes a flow path surface extending between the first side and the second side and a bonding surface opposite the flow path surface. The fan blade platform seal further includes a first seal portion including a first bonding segment including a first outer surface, mounted to the platform portion on the first side of the platform portion, and a first inner surface opposite the first outer surface. The fan blade platform seal further includes a stiffening portion mounted to the first inner surface. The stiffening portion includes a first bonding layer bonded to the first inner surface and a stiffening layer bonded to the first bonding layer on a first layer side of the stiffening layer.

Fan blade platform seal and method for forming same

A fire protection system for a gas turbine engine is disclosed. In various embodiments, the system includes a first fire blanket wall and a second fire blanket wall, the first fire blanket wall configured for attachment to a first fairing wall and the second fire blanket wall configured for attachment to a second fairing wall, and an attachment system configured to attach the first fire blanket wall to the first fairing wall and the second fire blanket wall to the second fairing wall.

Retention system for improved fire protection

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 17.2-18.2 inches (436-462 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 10.0-11.0 inches (255-281 mm). The airfoil element includes at least two of a first mode with a frequency of 51&#xb1;10% Hz, a second mode with a frequency of 147&#xb1;10% Hz, a third mode with a frequency of 267&#xb1;10% Hz, a fourth mode with a frequency of 350&#xb1;10% Hz, a fifth mode with a frequency of 454&#xb1;10% Hz and a sixth mode with a frequency of 619&#xb1;10% Hz.

Gas turbine engine airfoil frequency design

Systems and methods are provided related to manufacturing, repairing or otherwise providing an integrally bladed rotor. In one method, a set of preform rotor blades are arranged relative to a rotor disk. The preform rotor blades are concurrently bonded to the rotor disk.

Friction welding rotor blades to a rotor disk

Growing community of inventors

Sarasota, FL, United States of America

Jordan J Franklin