RING SEGMENT AND TURBOMACHINEA ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade existing in…DRIVE·Apr 8·1 min readFollowF01D11/08DOOSAN ENERBILITY CO LTD [KR]
RING SEGMENT AND TURBOMACHINEThe present disclosure proposes a ring segment and a turbomachine including the ring segment. The ring segment is installed on an inner circumferential surface of a casing and disposed to face an end …DRIVE·Jan 7·2 min readFollowF01D11/08DOOSAN ENERBILITY CO LTD [KR]
TIP SHROUD WITH EXIT SURFACE FOR COOLING PASSAGESA tip shroud (220) for a turbine blade (114) of a GT system (100) may include a body (240) coupled to a radial outer end (222) of an airfoil (202) of the turbine blade (114). The tip shroud (220) may …DRIVE·Feb 12·2 min readFollowF01D11/08GENERAL ELECTRIC TECHNOLOGY GMBH [CH]
SHROUD ASSEMBLY FOR GAS TURBINEA shroud assembly of a gas turbine includes: a holder including an insertion hole; a plate-shaped shroud main body covering the holder from a radially inner side and made of a ceramic matrix composite…DRIVE·Jun 12·1 min readFollowF01D11/08KAWASAKI HEAVY IND LTD [JP]
GAS TURBINE BLADE OUTER AIR SEAL WITH FACE SEALA blade outer air seal (64) includes a carrier (70), a ceramic seal segment (68), and a face seal (80). The ceramic seal segment (68) is supported on the carrier (70) and has first and second axial en…DRIVE·Feb 14·1 min readFollowF01D11/08RTX CORP [US]
SHROUD FOR A TURBOMACHINE AND CORRESPONDING ASSEMBLYA shroud (46) having an annular member (84) extending along an axis from a first end to a second end. The annular member has an inside surface (90) radially inward from an outside surface (92) that di…DRIVE·Nov 22·1 min readFollowF01D11/08HAMILTON SUNDSTRAND CORP [US]
ASSEMBLY, GAS TURBINE COMPRESSOR ROTOR AND PROCESS FOR SEALING A GAS TURBINE ENGINE COMPRESSOR ROTOR ASSEMBLYA double ring axial seal (50) for a disk (30) and blade (34) is provided. The disk (30) includes an array of blade slots (32) at a perimeter (31) of the disk (30) configured to receive a root portion …DRIVE·Oct 11·2 min readFollowF01D11/08RAYTHEON TECH CORP [US]
SYSTEM AND METHOD FOR OPTICAL MEASUREMENTS IN A ROTARY MACHINEA system is provided with a measurement system (27) having a sensor mount (82), a light source (16), a light sensor (18), and a controller (14) coupled to the light source (16) and the light sensor (1…DRIVE·Jul 5·1 min readFollowF01D11/08GEN ELECTRIC [US]
AIRFOIL WITH A SQUEALER TIP COOLING SYSTEM FOR A TURBINE BLADE, CORRESPONDING TURBINE BLADE, TURBINE BLADE ASSEMBLY, GAS TURBINE AND MANUFACTURING METHOD OF AN AIRFOILThe present invention provides an airfoil 110 with the squealer tip cooling system 50 for a turbine blade 100 at the blade tip 113, wherein the squealer tip cooling system 50 comprises a cooling passa…DRIVE·Jun 28·2 min readFollowF01D11/08DOOSAN ENERBILITY CO LTD [KR]
BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE AND CORRESPONDING ASSEMBLING/DISASSEMBLING METHODA blade outer air seal (64; 164) includes a carrier (70; 170) that has a dovetail (76; 176) and a ceramic seal segment (68; 168) supported on the dovetail (70; 170). The ceramic seal segment (68; 168)…DRIVE·Apr 26·1 min readFollowF01D11/08RAYTHEON TECH CORP [US]
Rotors for a gas turbine engine, corresponding gas turbine engine and methodA rotor (24) for a gas turbine engine includes a plurality of radially extending blades (28), each having a remote blade tip (30) defining an outer tip surface, and a leading edge (46) defined between…DRIVE·Sep 17·2 min readFollowF01D11/08PRATT & WHITNEY CANADA [CA]
Axial flow turbineProvided is an axial flow turbine that can enhance an effect of reducing a mixing loss. The axial flow turbine includes: a plurality of stator blades 2 provided on the inner circumferential side of a …DRIVE·Apr 30·2 min readFollowF01D11/08HITACHI LTD [JP]
GAS TURBINEA gas turbine is provided with: a turbine rotor blade (33); a turbine stator blade (32); a dividing ring (52) surrounding the turbine rotor blade (33) in a circumferential direction; an outer shroud (…DRIVE·Feb 5·2 min readFollowF01D11/08MITSUBISHI HEAVY IND LTD [JP]
Improvements in or relating to gas turbine engine controlA gas turbine engine control apparatus comprises a controller (34), a memory (36) associated with the controller (34) and inputs (38) for measurement data from an engine. The controller (34) determine…DRIVE·Jul 31·1 min readFollowF01D11/08ROLLS ROYCE PLC [GB]
Flow engine seal assemblyThe arrangement has shells (1-3) connected with one another in a circumferential direction (U) and arranged adjacent to each other in an axial direction (A). The shells comprise V or U-shaped cross se…DRIVE·Jul 24·1 min readFollowF01D11/08MTU AERO ENGINES GMBH [DE]
SPLIT RING COOLING STRUCTURE AND GAS TURBINEDisclosed is a split ring cooling structure of a gas turbine. The split ring cooling structure is provided with: first cooling channels arranged in the axial direction of the rotating shaft of split b…DRIVE·Dec 5·2 min readFollowF01D11/08MITSUBISHI HEAVY IND LTD [JP]
Gas turbine comprising a heat shield and method of operationThe present invention relates to a turbine (100), in particular a gas turbine. The turbine (100) comprises a first inner wall (101),a second inner wall (102), an inner casing (103) and a shield elemen…DRIVE·Oct 10·2 min readFollowF01D11/08SIEMENS AG [DE]
Gas turbine of the axial flow typeThe invention relates to a gas turbine (35) of the axial flow type, comprising a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air…DRIVE·May 30·2 min readFollowF01D11/08ALSTOM TECHNOLOGY LTD [CH]
GAS TURBINE FACILITYProvided is a gas turbine plant that enables active clearance control for ensuring tip clearance of first-stage turbine rotor blades required during start-up and for achieving the minimum tip clearanc…DRIVE·Oct 26·1 min readFollowF01D11/08MITSUBISHI HEAVY IND LTD [JP]
Adjustable fan case liner and mounting methodA liner for an interior surface of an engine casing (18), comprises a number of liner panels (32) disposed radially outwardly of a rotatable component (56) of the engine, such as a fan blade, and moun…DRIVE·Mar 2·1 min readFollowF01D11/08ROLLS ROYCE PLC [GB]
Fluid structure for a turbocompressorThe flow structure for the compressor of especially a gas turbine has at least one toroidal chamber (18) installed concentrically to an axis (17) of the compressor in the region of the free blade ends…DRIVE·Jan 11·1 min readFollowF01D11/08MTU AERO ENGINES GMBH [DE]
Coolable turbine shroud memberThe part (30) has a base plate that forms, in common with an associated control plate (38,44,52), a flow channel (36) for a coolant that extends in cross-section essentially over the entire width in r…DRIVE·Oct 9·1 min readFollowF01D11/08SIEMENS AG [DE]
Thermally charged wall structure and method to seal gaps in such a structureThe thermically-loaded wall (2), acted on by a hot gas (17), has 2 directly adjacent wall segments (33,35) separated by a gap (55) which is sealed by the thermic expansion of a flexure element (45) at…DRIVE·Jul 25·1 min readFollowF01D11/08SIEMENS AG [DE]
