Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 401 - 450 out of 22,991

Document Document Title
WO/2018/132084A1
The invention relates to a rotor (1) for a turbomachine (2) having an annular flow path (3) as seen in cross section, com-prising at least two shaft collars (5, 6) that are arranged axially adjacently and at a predetermined spacing, form...  
WO/2018/128609A1
A turbine rotating component (18) includes an airfoil (20) extending radially from a platform (40). An axial end face (44) of the platform (40) faces a seal gap (50) between the rotating component (18) and a stationary component (12). Th...  
WO/2018/127664A1
The invention relates to a part (1) comprising a substrate (3) with at least one portion made of a silicon-containing material adjacent to a substrate surface (S) and an environmental barrier (2) formed on the substrate surface and compr...  
WO/2018/129438A1
Various arrangements of a turbine for a rotating coalescer element of a crankcase ventilation system for an internal combustion engine are described. In some arrangements, the turbine is an impulse turbine, which is also known as a pelto...  
WO/2018/127652A1
The present invention relates to a part (1) comprising a substrate (3) with at least one portion made of a silicon-containing material adjacent to a substrate surface (S) and an environmental barrier (2) formed on the substrate surface a...  
WO/2018/123045A1
A scroll part of a turbine housing is configured such that a concave distribution is included in at least part of a first graph of which the horizontal axis is an angular position θ in the circumferential direction of the scroll part an...  
WO/2018/115763A1
A turbomachine (10) comprising a fan (12) shaft driven by a turbine shaft (16) by the intermediary of a rotational speed reduction device (20), said turbomachine comprising decoupling means (28) interposed between the reduction device (2...  
WO/2018/116333A1
A turbine rotor blade assembly characterized in that in the two-dimensional coordinates shown in fig. 5, A, CF, T, and L given below are set so as to satisfy 1.2 × 105 ≤ (A × CF)/(T × L) ≤ 17 × 105. Formula (1): (A × CF)/(T × L...  
WO/2018/114766A1
The invention relates to a method for joining hot gas component segments (6, 7), comprising the following steps: providing the segments (6, 7) to be joined; applying complementary joining elements (8) to the surface of the segments (6, 7...  
WO/2018/119391A1
A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back w...  
WO/2018/093627A3
An assembly comprises a cooling chamber (102) disposed inside an airfoil (100) of a turbine assembly. The cooling chamber (102) is configured to direct cooling air inside of the airfoil (100). The assembly includes an impingement hole (1...  
WO/2018/114659A1
A method for producing a wind turbine rotor blade (200) is disclosed. The wind turbine rotor blade (200) has at least one inner blade section (210) and an outer blade section (220) as well as a connection element (600). The inner blade s...  
WO/2018/111407A1
The present disclosure generally relates to integrated core-shell investment casting molds that provide filament structures corresponding to cooling hole patterns in the surface of the turbine blade or stator vane, which provide a leachi...  
WO/2018/108458A1
This invention relates to a gas turbine blade (10), which has a suction side (11) and a pressure side (12) during regular use and which also has at least one internally arranged chamber (15), which is designed to conduct a cooling fluid ...  
WO/2018/110580A1
This gas turbine disassembling/assembling method is configured such that a gas turbine is provided with: a seal plate (44) that is provided to one side in an axial direction with respect to a rotor disk (18); and a seal plate movement re...  
WO/2018/108393A1
The invention relates to an anti-icing turbomachine blade (26), in particular for a low-pressure compressor or an intermediate-pressure compressor of a turbomachine. The blade (26) has a leading edge (28) formed by an ice-phobic surface ...  
WO/2018/111276A1
A gas turbine engine locates the rotating flange joint (25) in the pre-swirl section (20). The rotating flange joint (25) joins the compressor section (4) and the turbine section (6). The fluid flow typically used for the pre-swirl secti...  
WO/2018/111489A1
A method of selectively applying an overlay coating to a coated article and a selectively treated coated article are provided. The method includes the steps of providing the coated article having a treatment region that includes a bond c...  
WO/2018/110581A1
This gas turbine disassembling/assembling method is configured such that a gas turbine is provided with: a seal plate that is provided to one side in an axial direction with respect to a rotor disk; and a seal plate movement restriction ...  
WO/2018/111408A1
The present disclosure generally relates to integrated core-shell investment casting molds including a main core portion, a core tip portion, and a shell portion with at least one cavity between the core portion and the shell portion. Th...  
WO/2018/110827A1
The present invention provides a partial admission operation turbine apparatus comprising: a rotor portion rotatably coupled to a rotary shaft of a turbine and including a plurality of rotor blades; a nozzle portion fixedly coupled to th...  
WO/2018/110584A1
This gas turbine disassembling/assembling method comprises a seal plate restriction state switching step for switching between a seal plate unrestricted state where a seal plate movement restriction part does not restrict radial movement...  
WO/2018/103990A1
Intermediate bond-coat layer for improvement of adherence of a thermal barrier coating on a ceramic matrix composite substrate By application of aluminum or aluminum alloy (7') in an intermediate step a good ceramic coating (7) in an adh...  
WO/2018/104678A1
The invention proposes a method for simulating the distribution of blades on a turbomachine disc, the method comprising the steps of:⋅providing a plurality of blade configurations, each blade configuration being associated with a blade...  
WO/2018/103995A1
The invention relates to a method for producing a gas turbine component (1), which, during gas turbine operation in the mounted state as intended, comes into frictional contact with at least one friction partner, wherein the method has t...  
WO/2018/106539A1
A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine positioned within the housing. The fluid causes the turbine to rotate about a center rotational axis within the housing. The turbine c...  
WO/2018/103994A1
The use of magnesium oxide, reactive alumina and aluminium oxide as a base provides for a new erosion-resistant material upon sintering.  
WO/2018/103996A1
Continuous cracks can be optimally repaired using CMT technology by using a fluxed-core wire of solder material with a filling consisting of solder material and base material.  
WO/2018/101632A1
The disclosure relates to a carbon blade for a wind turbine with multiple down conductors, and more particularly, to a carbon blade for a wind turbine with multiple down conductors that includes multiple down conductors disposed thereon ...  
WO/2018/101303A1
This gas turbine high-temperature component is provided with: a body; a porous part through which a cooling gas can pass and which is provided as at least a part of the body or on at least a part of the body; and at least one filter that...  
WO/2018/100160A1
The invention relates to a gas turbine having at least one disk (5), wherein turbine blade elements (1) are connected by a connecting means (2) to the at least one disk (5), characterized in that the connecting means (2) in the interior ...  
WO/2018/101190A1
A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat l...  
WO/2018/095708A1
By roughening the surface of a CMC substrate with a plasma spray device using the same plasma gun for roughening and coating by adjusting spraying parameters, good adhering and coating of the ceramic layer on a CMC substrate is yielded o...  
WO/2018/094536A1
The present disclosure generally relates to rotary turbomachinery methods and integrated processes requiring high-energy efficiency. In one embodiment, the present invention relates to rim-rotor configurations enabling long-term survival...  
WO/2018/097832A1
The present invention generally relates to high g-field combustion methods and integrated processes requiring high-energy efficiency and low NOx emissions to maximize fuel productivity and integrated process production output. In one emb...  
WO/2018/093808A1
A turbocharger turbine wheel member with stiffener members thereon, together with a method of manufacture therefor are disclosed. The stiffener members are molded integrally on the turbine wheel blade members. The stiffener members, as w...  
WO/2018/093473A1
Various aspects include a turbomachine bucket (20), such as a steam turbine bucket, a corresponding shim (52) and a related turbine rotor. The steam turbine bucket includes a blade (22) having a first end, and a second end opposite the f...  
WO/2018/093627A2
An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber is configured to direct cooling air inside of the airfoil. The assembly includes an impingement hole disposed inside the airfoi...  
WO/2018/087808A1
This rotary machine comprises: a pair of radial bearings (102) for supporting a rotating shaft (103) so that the rotating shaft (103) can rotate about a center axis (C); impellers (104) affixed to the rotating shaft (103) at positions se...  
WO/2018/087945A1
A sliding member (10) with an abrasion-resistant coating film is provided with a sliding member (12) and an abrasion-resistant coating film (14) that is provided on the sliding surface of the sliding member (12). The abrasion-resistant c...  
WO/2018/087701A1
The present invention relates to a method for the construction of rotor and stator elements for turbomachinery comprising: preparing a solid (14) of material to be machined; performing cuts (15', 15", 15'", 15"", 22', 22", 22'", 22"") in...  
WO/2018/087452A1
The invention relates to a turbomachine part (30) coated with at least one first thermal barrier layer (33) comprising a ceramic material and first ceramic fibers (34) dispersed in said first layer. The first layer may comprise a gradien...  
WO/2018/087487A1
The invention relates to a process for manufacturing a turbomachine blade (P) of the type having at least one 3D cavity (7), characterized in that said blade is produced by a succession of depositions and selective consolidations of laye...  
WO/2018/087370A1
The invention relates to a turbomachine rotor (10) comprising a radially inner hub element (11), a radially outer cover element (12), and rotor blades (13) which extend between the hub element (11) and the cover element (12) and have rot...  
WO/2018/026413A3
An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the...  
WO/2018/084902A1
A turbofan engine includes a core (30); and a low-pressure turbine (22) configured to drive a fan (46) to produce a fan flow that exits the engine without passing through a turbine. The fan includes a rotor having at least one rotor stag...  
WO/2018/077589A1
The invention relates to a turbine rotor arrangement and to a method of manufacturing a turbine rotor blade. The arrangement comprises a rotor disk (2) and a rotor blade (3) with a blade root (4), the blade root comprising, with respect ...  
WO/2018/080416A1
A turbine airfoil (10) includes a radially extending hollow rib (26) positioned in a radial cavity (40) defined between chord-wise spaced partition walls (24). The hollow rib (26) is spaced from a pressure sidewall (16) and from a suctio...  
WO/2018/080699A1
A propeller blade (18) spanning radially from a root (32) to a tip (34) and spanning axially from a leading edge (36) to a trailing edge (38) spaced from the leading edge forming an airfoil (39) therebetween where a sweep line (62) can b...  
WO/2018/076050A1
A multi-stage axial turbine (typically between 4 and 10 stages) designed to operate more efficiently with partial admission of low temperature steam in each stage except the last one or two stages. Each stage of the subject turbine opera...  

Matches 401 - 450 out of 22,991