Mistuned fan
I Theratil, KP Balike, R Ivakitch, SM Kelly… - US Patent …, 2019 - Google Patents
(57) ABSTRACT A compressor rotor for a gas turbine engine is described which includes
sets of blades having different airfoil thick ness distributions, each including a frequency …
sets of blades having different airfoil thick ness distributions, each including a frequency …
Gas turbine engine having a mistuned stage
J Xu, FT Tenney - US Patent 10,302,100, 2019 - Google Patents
A stage of a gas turbine engine according to an exemplary aspect of the present disclosure
includes, among other things, a row of flow directing components circumferentially disposed …
includes, among other things, a row of flow directing components circumferentially disposed …
Fan rotor with flow induced resonance control
I Theratil, K Balike - US Patent 10,823,203, 2020 - Google Patents
A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor
blades, the first set of rotor blades having a baseline profile and the second set of rotor …
blades, the first set of rotor blades having a baseline profile and the second set of rotor …
Guide vane segment for a turbomachine
M Schlemmer, M Pernleitner, N Wolfrum… - US Patent …, 2019 - Google Patents
The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet
engine, having at least two vanes that are joined together by way of at least one common …
engine, having at least two vanes that are joined together by way of at least one common …
Axial fan with unbalanced blade spacing
RJ Van Houten, Y Shin - US Patent 10,480,527, 2019 - Google Patents
An axial fan comprising a hub and a plurality of blades extending from a periphery of the
hub. Each of the blades has a thickness which varies from a leading edge to a trailing edge …
hub. Each of the blades has a thickness which varies from a leading edge to a trailing edge …
Mistuned fan for gas turbine engine
T Veitch, F Abrari, E Adique, D Fudge… - US Patent …, 2020 - Google Patents
A fan for a gas turbine engine comprises blades distributed around a hub. The blades
include first and second blades, having geometric parameters and/or material properties that …
include first and second blades, having geometric parameters and/or material properties that …
Flutter avoidance through control of texture and modulus of elasticity in adjacent fan blades
MG Glavicic - US Patent App. 15/269,540, 2018 - Google Patents
A fan for a turbofan engine includes a plurality of blades and a disk, the plurality of blades
constructed of an anisotropic material, the anisotropic material is a plate, sheet, or forging. A …
constructed of an anisotropic material, the anisotropic material is a plate, sheet, or forging. A …
Fan rotor with flow induced resonance control
I Theratil, K Balike - US Patent 10,458,436, 2019 - Google Patents
A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor
blades, the first set of rotor blades having a baseline profile and the second set of rotor …
blades, the first set of rotor blades having a baseline profile and the second set of rotor …
Fan rotor with flow induced resonance control
I Theratil, K Balike - US Patent 10,480,535, 2019 - Google Patents
A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor
blades, the first set of rotor blades having a baseline profile and the second set of rotor …
blades, the first set of rotor blades having a baseline profile and the second set of rotor …
Compressor rotor for supersonic flutter and/or resonant stress mitigation
I Theratil, KP Balike, A Abate, S Kelly… - US Patent …, 2020 - Google Patents
A compressor rotor, such as a fan, for a gas turbine engine is described which includes
alternating at least first and second blade types. The leading edge of the second blade types …
alternating at least first and second blade types. The leading edge of the second blade types …