Abstract:
The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge.
Abstract:
A pulse valve arrangement includes a valve housing on which is fixed a control valve The valve housing includes a circular cylindrical portion with a valve member movably arranged therein. The valve chamber has an inlet adapted to be connected to a pressure medium source for allowing pressure medium to flow into the valve chamber and an outlet through which pressure medium flows out of the valve chamber. The control valve may be closed in which the outlet of the valve chamber is moved to a closing position blocking the flow of pressure medium, or may be opened in which the outlet of the valve chamber is moved to an opening position allowing a pulse of pressure medium therethrough. The valve member within the valve housing is freely displaceable within the circular cylindrical portion of the valve housing based on the pressure within the valve chamber as controlled by the control valve.
Abstract:
Pulse valves and methods of using pulse valves are provided. The pulse valves include a dampening mechanism to decrease mechanical stresses, decrease operating noise, decrease compressed air waste and increase operational life expectancy. Such dampening mechanism is arranged within an internal area of the pulse valve housing. Additionally, fluid within the internal area of the pulse valve provides cushioning effects during operation of the pulse valve.
Abstract:
A stator component of a turbomachine is composed substantially of at least one axially extending outer ring (10) which serves as a frame of an inner ring composed of partial segments (20). The partial segments are arranged on one another such that, on the rotor side, they form a coherent circular circumferential surface in relation to the rotational movement of rotor blades (30). The individual partial segment (20) is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behaviour as a function of the load ranges of the turbomachine.
Abstract:
The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine. The can combustor includes an essentially cylindrical casing with an axially upstream front panel and an axially downstream outlet end. The can combustor further includes a number of premixed burners, extending in an upstream direction from said front panel and having a burner exit, supported by this front panel, for supplying a fuel/air mixture into a combustion zone inside the casing. Up to four premixed burners are attached to the front panel in a substantially annular array. Each burner has a conical swirl generator and a mixing tube to induce a swirl flow of said fuel/air mixture.
Abstract:
The invention refers to a device for positioning the rotor of a gas turbine linearly actuating a piston rod that actuates on its end a ratched wheel that moves the rotor of the gas turbine. The device includes an eccentric wheel and a synchronous motor, such that the piston rod is moved through the eccentric wheel, connected to the synchronous motor. The device also includes an incremental counter controlling the angular position of the synchronous motor.
Abstract:
Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions located in the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.
Abstract:
An apparatus and a method are provided for the inspection of ferromagnetic components using magnetic particles, particularly for in-situ inspection of parts of power plants, with the apparatus including a movable chassis defining a magnetic yoke with a central opening over a surface of the component to be inspected and a discharge nozzle to inject the magnetic particles onto the surface, a magnetic field source for generating a magnetic field on at least part of the surface below the opening and a probe to measure a representation of the spatial distribution of the magnetic particles on the surface.
Abstract:
A combustion chamber including a body with a fuel supply duct for supplying a fuel into the body and a carrier air supply duct for supplying air into the body. An adjusting system adjusts the carrier air mass flow supplied into the body according to the features of the fuel.
Abstract:
The invention relates to a method for additively manufacturing an article made of a difficult-to-weld highly-precipitation-strengthened Ni-base super alloy that comprises Al and Ti in the sum of more than 5 wt.-% or a difficult-to weld carbide/solution-strengthened cobalt (Co)-base super alloy, whereby a metal particle mixture of at least a first phase and a second phase is provided as a starting material, said first phase of the mixture being a base material and said second phase of the mixture being a material which is a derivative of the first material and has relative to said material of said first phase an improved weldability, and whereby the metal particle mixture is processed by means of an additive manufacturing process which is one of selective laser melting (SLM), selective laser sintering (SLS), electron beam melting (EBM), laser metal forming (LMF), laser engineered net shape (LENS), or direct metal deposition (DMD).