F - Mech Eng,Light,Heat,Weapons – 02 – K
Patent
F - Mech Eng,Light,Heat,Weapons
02
K
F02K 3/06 (2006.01) F01D 5/14 (2006.01) F04D 29/32 (2006.01)
Patent
CA 2335321
This invention concerns a turbofan gas turbine engine with an integrated fan and low pressure compressor rotor which is mounted to a forward end of the shaft immediately upstream of a one piece engine support structure (20). The fan blade portion (30) and compressor blade portion (31) have aerodynamically aligned lateral airfoil surfaces and platforms as enabling a single integrated rotor to replace prior art separate blades thereby simplifying the engine design and reducing the axial length of the engine.
L'invention concerne un moteur à turbine à gaz et à turbosoufflante, comprenant un rotor de compresseur à basse pression et à soufflante intégrée, lequel rotor est monté sur une extrémité avant de l'arbre, située immédiatement en amont d'une structure monobloc (20) de support du moteur. La portion (30) des pales de la soufflante et la portion (31) des pales du compresseur présentent des surfaces et plates-formes profilées latérales, alignées de manière aérodynamique, permettant à un seul rotor intégré de remplacer les pales séparées de la technique existante, simplifiant ainsi la conception du moteur et réduisant la longueur axiale de celui-ci.
Norton Rose Or S.e.n.c.r.l. S.r.l./llp
Pratt & Whitney Canada Corp.
Pratt & Whitney Canada Corp./pratt & Whitney Canada Cie.
LandOfFree
Integrated fan/low pressure compressor rotor for gas turbine... does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Integrated fan/low pressure compressor rotor for gas turbine..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Integrated fan/low pressure compressor rotor for gas turbine... will most certainly appreciate the feedback.
Profile ID: LFCA-PAI-O-1758285