Pratt-whitney Canada Corp

Aleksander Kojovic

Lev Alexander Prociw

Jun Shi

Harris Shafique

Shaoluo L Butler

David C Jarmon

David C Jamon

Lev A Prociw

A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.

Reverse flow ceramic matrix composite combustor

A combustor swirler for a gas turbine engine and method of manufacturing by metal injection molding an inner component and an outer cylindrical component. Indentations are molded in one of the inner and outer components and sealed by the engagement of the components together to form a series of fluid flow passages. The inner and outer components are molded with interlocking features for ensuring proper alignment of the components during assembly.

Method of manufacturing a metal injection moulded combustor swirler

A fuel manifold for a gas turbine engine having a first peripheral surface having a first channel defined therein and a second peripheral surface having a second channel defined therein, each of the first and second channels being sealingly enclosed to define a corresponding conduit.

Multi-channel fuel manifold

Growing community of inventors

Oakville, Canada

Aleksander Kojovic