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WO/2017/209853A1 |
A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembl...
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WO/2017/209752A1 |
An attachment system (30) for securing a turbine blade (14) to a rotor disc (11) includes a root (28). In a plane perpendicular to a rotor axis (6), the root (28) is asymmetric about a radially extending longitudinal root axis (8). The r...
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WO/2017/207615A1 |
Expander (4) for use at a maximum internal operating temperature of less than or about 180°C, comprising a stationary shroud (25), a plurality of blades (10) or shrouded blades (10') arranged circumferentially about a rotor (30) and ext...
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WO/2017/205680A1 |
A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.
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WO/2017/203917A1 |
Provided is a rotating body comprising: an impeller having a body 21, the impeller also having a surface 23 on which welding is to be performed, the surface 23 being provided on the rear surface 21b of the body 21, the impeller further h...
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WO/2017/205246A1 |
The present application provides a steam turbine. The steam turbine may include a number of rotor wheel slots (130), a number of buckets (120) positioned in the rotor wheel slots (130), and a radial support assembly positioned between ea...
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WO/2017/204941A1 |
The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plu...
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WO/2017/200549A1 |
A turbine blade tip shroud (22) includes a shroud base (20) extending in a circumferential direction of a turbine engine (64) and further extending in an axial direction of the turbine engine (64) from an upstream edge (56) to a downstre...
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WO/2017/200401A1 |
A component and method of forming a component are disclosed. The component includes a cast alloy section and an additive manufacturing section secured to the cast alloy section. Both the cast alloy section and the additive manufacturing ...
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WO/2017/200670A1 |
The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud ...
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WO/2017/200828A1 |
A turbine rotor shaft assembly (16) and associated turbocharger (10) that includes at least one turbine rotor member (17) having a first face (42) and an opposed second face (44); and a rotor shaft (18) having a first end (49) and an opp...
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WO/2017/200652A1 |
A method of damping a vibration in a rotatable member and a damping system for a rotatable machine are provided. The damping system includes one or more damping stages. The rotatable machine further comprising a casing at least partially...
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WO/2017/196498A1 |
An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include a skin layer and a porous layer. The skin layer can include a skin cooling cir...
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WO/2017/194860A1 |
A turbine ring assembly comprises a plurality of ring sectors (10) made of a ceramic matrix composite material and forming a turbine ring and a ring support structure (3) comprising a first and a second annular flange (32, 36). Each ring...
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WO/2017/195518A1 |
Provided is a coating structure, a turbine part having the same, and a method for manufacturing the coating structure. The coating structure is provided on a surface of a base portion including a ceramic-based composite material. The coa...
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WO/2017/195094A1 |
A mixed flow turbine (1) for the expansion phase of steam thermodynamic cycles of an organic Rankine cycle provided with a first section (A) in which a first expansion of a main flow of working fluid takes place, in a substantially radia...
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WO/2017/196698A1 |
An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling c...
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WO/2017/194886A1 |
The present invention relates to a composite part comprising at least: - a fibrous reinforcement comprising silicon carbide fibers having an oxygen content of less than or equal to 1% as an atomic percentage, and - a matrix present in th...
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WO/2017/196905A1 |
A coating system disposed on a surface of a substrate is provided. The coating system includes a bond coating on the surface of the substrate, a protective coating on the bond coating, a thermal barrier coating on the protective coating,...
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WO/2017/196298A1 |
A component for a combustion turbine engine has a ceramic matrix composite ("CMC") central substrate (73); with a substrate rib (77) that bridges opposed substrate sidewalls (74, 76). The central substrate (73) includes an embedded first...
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WO/2017/192247A1 |
A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil ...
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WO/2017/191071A1 |
A system for cooling a blade (38) in a rotor (22) of a gas turbine (10), the blade (38) comprising: - a root (122) for connecting the blade (38) to the rotor (22), - an aerofoil (126) connected to the root (122), - a cooling passage exte...
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WO/2017/190884A1 |
The invention relates to a turbine housing (21) for a turbocharger (1) of an internal combustion engine, comprising - an annular duct (22) for guiding an exhaust gas mass flow (AM) to a turbine wheel (12) that can be arranged in the turb...
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WO/2017/191075A2 |
A turbomachine component, such as a blade or a vane, is presented. The turbomachine component has an aerofoil. The aerofoil includes a suction side wall and a pressure side wall bordering an aerofoil cavity. The turbomachine component ha...
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WO/2017/190978A1 |
A gas turbine section with improved strut design A gas turbine section for an annular gas path is presented. The annular gas path is defined through a gas turbine engine. The gas turbine section includes an inner and an outer gas path wa...
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WO/2017/186492A1 |
The invention relates to a method for profiling blades of an axial turbomachine, having the steps of: a) preparing a geometric model of a blade profile (R, -1, +1); b) determining an oscillation mode of the geometric model; c) calculatin...
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WO/2017/186481A1 |
The invention relates to a cooling fluid distributor for distributing cooling fluid in a cavity of a turbomachine blade, having at least two partial inserts (3, 5), wherein the partial inserts (3, 5) are introduced individually into the ...
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WO/2017/189291A1 |
The present disclosure relates to a turbine wheel for a turbine of an exhaust gas turbocharger. The turbine wheel has a base body comprising a back wall and a plurality of turbine blades, connected to the base body, which each comprise a...
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WO/2017/189208A1 |
A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed...
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WO/2017/186661A1 |
The present invention provides a gas turbine blade and a gas turbine, the gas turbine blade comprising: a blade profile, with a gas cooling channel provided in the blade profile; and a top sealing cover, disposed at the top of the blade ...
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WO/2017/188991A1 |
A staged cooling system for turbine component (10) includes a near-wall cooling channel (80) defined between an outer wall (12) of the turbine component (10) and a hollow core (30) positioned in an internal cavity (24) of the turbine com...
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WO/2017/186640A1 |
The invention relates in general to rotor blades and/or guide blades for a blading, that is to say the blades of a compressor or of a turbine. The invention also relates to a method for producing such a rotor blade or guide blade. The in...
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WO/2017/187050A1 |
A method for producing a part from composite material comprises positioning a fibrous texture (10) in a mould (110) comprising, in the lower portion of same, a part made from porous material (130) on which a first face (10b) of the textu...
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WO/2017/182423A1 |
The invention relates to a guide vane (1) for a fluid flow machine, in particular gas turbine, having an outer platform (2) in the properly mounted state of the guide vane, a vane leaf (6) projection from the outer platform (2), which ex...
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WO/2017/184138A1 |
A preloaded snubber assembly for turbine blades includes a plurality of turbine blade airfoils (10) including a trailing edge and a leading edge joined by a pressure side and a suction side to provide an outer surface (14) extending in a...
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WO/2017/182322A1 |
Guide vane (1) for a turbomachine having, in the properly installed state, an outer platform (2), a blade airfoil (3) protruding from the outer platform, extending in a longitudinal direction and defining a cavity (4) in its interior, an...
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WO/2017/180100A1 |
A gas turbine engine component (100) formed of material having phononic regions (30). The phononic regions (30) are formed of alloys or allotropes of the material (20). The phononic regions (30) modify the behavior of the phonons (10) an...
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WO/2017/180102A1 |
A gas turbine engine component (100) formed of material (20) having phononic regions (30). The phononic regions are formed of non-metallic nanostructures (35). The phononic regions (30) modify the behavior of the phonons (10) and control...
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WO/2017/180101A1 |
A gas turbine engine component (100) formed of material having phononic regions (30). The phononic regions (30) are formed of doped nanostructures (35). The phononic regions (35) modify the behavior of the phonons (10) and control heat c...
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WO/2017/179711A1 |
A steam turbine rotor blade equipped with an extension part (7) that is provided at the tip-end portion in the blade height direction of a blade main body (61) on which a front edge part (61a) is formed, and that extends from a negative-...
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WO/2017/178747A1 |
The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24...
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WO/2017/180104A1 |
A gas turbine engine component (100) formed of material (20) having phononic regions (30). The phononic regions (30) are formed of void nanostructures. The phononic regions (30) modify the behavior of the phonons (10) and manage heat con...
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WO/2017/180117A1 |
There is provided a component (30) formed from a plurality of laminates (10, 32) stacked on one another, thereby defining a stacked laminate structure (25) having a leading edge (18) and a trailing edge (20). Each of the plurality of lam...
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WO/2017/180105A1 |
A gas turbine engine component (100) formed of material having phononic regions (30). The phononic regions (30) are formed of anisotropic nanostructures (35) that are oriented in different directions than the bulk of the material forming...
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WO/2017/176723A1 |
A turbine blade (10) includes a platform (12) with an internal cavity (13) formed therein and an airfoil (14) extending radially from the platform. The turbine blade includes a first portion (20) made from ceramic matrix composite materi...
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WO/2017/174355A1 |
The invention relates to a rotor disk assembly having a rotor disk (01), on which a plurality of sealing plates (11) is arranged in front of an end side (02) and wherein a plurality of separate sealing vanes (21) are arranged radially ou...
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WO/2017/175563A1 |
Provided are a nickel-base alloy having high high-temperature strength, a turbine blade using same, and a method for producing an injection molded article of the nickel-base alloy. The nickel-base alloy (10) contains: at least one metal ...
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WO/2017/174723A1 |
The invention relates to a seal on a rotor disk assembly having a rotor disk (01), which rotor disk (01) has a plurality of axially extending blade-retaining grooves (09) distributed on the outer periphery. Furthermore, the rotor disk as...
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WO/2017/168335A1 |
The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different ...
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WO/2017/168766A1 |
A rotary machine blade (31) equipped with a clearance flow suppression blade section (34), the lean angle of which has one or more inflection points, and which is formed such that when the direction from a positive-pressure surface (31a)...
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