公开(公告)号：US11499432B2

公开(公告)日：2022-11-15

申请号：US15741374

申请日：2016-07-01

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Vivien Mickaël Courtier ,  Adrien Louis Nicolas Laurenceau ,  Dominique Gerhadt Mayhew ,  Jonathan Evert Vlastuin

IPC: F01D5/16 ,  F01D5/14 ,  B64D27/00

Abstract: A method of altering the twisting relationship for the aerodynamic surface of a fan blade of a gas turbine engine, wherein the following steps are performed: establishing, for a portion of the aerodynamic surface of the fan blade, an alteration relationship defined by variation of a pitch angle of the blade as a function of radial height along the blade, the alteration relationship including alterations that are each defined by a height along with the radial height of the fan blade and by an amplitude; and applying the alteration relationship as established in this way to an initial twisting relationship of the fan blade so as to obtain an altered twisting relationship for the fan blade, the initial twisting relationship being defined by a polynomial for the radial height of the fan blade as a function of its pitch angle.

公开(公告)号：US11046424B2

公开(公告)日：2021-06-29

申请号：US15506937

申请日：2015-08-28

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Clement Marcel Maurice Dejeu ,  Jonathan Evert Vlastuin ,  Mathieu Simon Paul Gruber

IPC: B64C11/06 ,  B64C11/48 ,  B64C11/30 ,  F02K3/072 ,  F01D1/26 ,  F01D7/00 ,  B64D27/00 ,  F04D29/36

Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

公开(公告)号：US11591913B2

公开(公告)日：2023-02-28

申请号：US15507071

申请日：2015-08-28

Applicant: Safran Aircraft Engines

Inventor： Clement Marcel Maurice Dejeu ,  Jonathan Evert Vlastuin ,  Mathieu Simon Paul Gruber

IPC: F01D5/14 ,  B64C11/30 ,  F02K3/072 ,  F01D1/26 ,  B64C11/06 ,  F01D7/00 ,  F01D5/06 ,  B64D27/00

Abstract: A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.

公开(公告)号：US11421603B2

公开(公告)日：2022-08-23

申请号：US17278149

申请日：2019-09-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nathalie Nowakowski ,  Gilles Alain Marie Charier ,  Kévin Morgane Lemarchand ,  Nicolas Jérôme Jean Tantot ,  Jonathan Evert Vlastuin ,  Henri Yesilcimen

IPC: F02C7/36 ,  F02C7/06 ,  F02K3/06

Abstract: Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.

公开(公告)号：US11891967B2

公开(公告)日：2024-02-06

申请号：US17277801

申请日：2019-09-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Henri Yesilcimen ,  Caroline Marie Frantz ,  Nicolas Jérôme Jean Tantot ,  Nathalie Nowakowski ,  Gilles Alain Marie Charier ,  Kévin Morgane Lemarchand ,  Jonathan Evert Vlastuin

IPC: F02K5/00 ,  F02C6/20 ,  F02K3/00 ,  F01D15/10 ,  F02K3/06 ,  B64D27/02

CPC classification number: F02K5/00 ,  F01D15/10 ,  F02C6/20 ,  F02K3/00 ,  F02K3/06 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2220/70 ,  F05D2220/76 ,  F05D2260/40311

Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.

公开(公告)号：US11772777B2

公开(公告)日：2023-10-03

申请号：US17341277

申请日：2021-06-07

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Clement Marcel Maurice Dejeu ,  Jonathan Evert Vlastuin ,  Mathieu Simon Paul Gruber

IPC: B64C11/06 ,  B64C11/32 ,  B64C11/30 ,  F02K3/072 ,  F01D1/26 ,  F01D7/00 ,  B64C11/48 ,  B64D27/00 ,  F04D29/36

CPC classification number: B64C11/30 ,  B64C11/06 ,  B64C11/32 ,  B64C11/48 ,  F01D1/26 ,  F01D7/00 ,  F02K3/072 ,  B64D2027/005 ,  F04D29/362 ,  F05D2220/325 ,  F05D2220/36 ,  F05D2250/314 ,  F05D2260/74 ,  F05D2260/79 ,  F05D2260/961 ,  Y02T50/60

Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

公开(公告)号：US11047238B2

公开(公告)日：2021-06-29

申请号：US16478972

申请日：2018-01-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Damien Bernard Emeric Guegan ,  Prasaad Cojande ,  Pierre-Hugues Ambroise Maxime Victor Retiveau ,  Jonathan Evert Vlastuin

IPC: F01D5/14 ,  F04D29/32

Abstract: A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane wheel defining an axis, the vane having an airfoil presenting a leading edge and a trailing edge, the leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation, said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from the first end of the airfoil.

公开(公告)号：US10669010B2

公开(公告)日：2020-06-02

申请号：US15569639

申请日：2016-04-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Sébastien Emile Philippe Tajan ,  Adrien Jacques Philippe Fabre ,  Adrien Louis Nicolas Laurenceau ,  Jonathan Evert Vlastuin ,  Laurence Francine Vion

IPC: B64C11/06 ,  F01D5/02 ,  F01D7/00 ,  B64D27/10 ,  B64D27/00

Abstract: The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes (33) located radially outside the nacelle in order to be traversed by a secondary jet (31) flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (33), each vane (33) comprising a blade extending from a root that is used to removably attach same to a base of the associated support (34). Each base (36) is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base (36) and the vane root supported by the base (36) is surrounded and covered by a detachable aerodynamic cover (37).

公开(公告)号：US10387611B2

公开(公告)日：2019-08-20

申请号：US15517185

申请日：2015-10-08

Applicant: Safran Aircraft Engines

Inventor： Cyril Verbrugge ,  Clement Marcel Maurice Dejeu ,  Anthony Pascal Eloi Louet ,  Jonathan Evert Vlastuin

IPC: G06F17/50 ,  B64C11/18 ,  B64D27/00

Abstract: A method for modeling an offset portion of a blade of a non-ducted propeller is provided. The method includes: parametrizing a C1-class curve representing a deformation of the blade characterizing the offset, according to a position along a section at a given height in the blade, the curve intersecting consecutively through a first bend control point, a central control point, and a second bend control point, the first and second bend control points defining the extent of the blade section, the parametrization being implemented according to a first deformation parameter defining the abscissa of the central control point, a second parameter of deformation defining the ordinate of the second bend point, and a third deformation parameter defining the angle of the tangent to the curve at the second bend control point; optimizing one of the deformation parameters; and plotting the values of the optimized parameters on an interface.