Abstract: A fluid flow machine has a main flow path, in which at least one row of blades (1) is arranged, and a shroud (2), which is embedded in a recess (3) of a component, with the component and the blades (1) being in relative rotational movement to each other. The assembly forming the shroud includes at least one internal chamber (7) which is suppliable with fluid from a source. The at least one internal chamber (7) is connected to the main flow path surrounding the blades (1) or to a cavity (9) surrounding the shroud (2) via at least one outlet (8) which is arranged on one side of the shroud (2). The shape of the outlet (8) and the shape of the outlet opening are such that a fluid barrier jet is generated at the outlet (8), which stops recirculation of fluid through the shroud cavity (9).

Abstract: A fluid flow machine has a flow path provided by a casing (1) and a rotating shaft (2), in which rows of rotor blades (3) and stator blades (4) are arranged, and includes at least one annular groove-type recess (5) being disposed in a blade (3, 4) tip area in an annulus duct wall of the casing (1) and/or the shaft (2). An upstream end point (E) of the recess (5) in a flow direction is set at a distance (e)>0 forward of a forward blade tip point (A), and a downstream end point (F) of the recess (5) is set at a distance (f) rearward of point (A), where: 0.5 L>(f)>0, and L is a distance between point (A) and a rearward blade tip point (B).

Abstract: A blade of a fluid-flow machine has at least one cavity 2 arranged in the blade 1, with the cavity 2 connecting to a fluid supply, and at least one outlet opening 3 connecting the cavity 2 to a flow path, in which the blade 1 is arranged. The outlet opening 3 is of a nozzle-type design and essentially inclined in a direction of a main flow extending longitudinally to a corresponding surface of the blade 1. The outlet opening 3 extends over at least a part of the blade 1 height and the outlet opening 3 forms a step in a contour of the blade 1 profile, with a fluid jet issuing from the outlet opening 3 essentially tangentially attaching onto the blade surface.

Abstract: A fluid-flow machine has a main flow path, in which at least one row of blades (1) is arranged, and a shroud (2) embedded in a cavity (3) of a component, with the component and the blades being in rotary movement relative to each other. The shroud (2), as referred to an axial direction of the fluid-flow machine is arranged between two reference points (A) and (B) at the periphery of the main flow path of the fluid-flow machine and projects beyond a rectilinear connection of the reference points (A) and (B) into the flow path in at least one location of the circumference and in at least one of the areas of the leading or trailing edge of the appertaining blade row.

Abstract: A blade of a fluid-flow machine has a cross-section, which in at least one part of the blade height in at least one flow-line profile section is formed by at least two partial profiles separated from each other, with each of the individual partial profiles having the shape of a blade profile.

Abstract: A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing with at least one inner volume, through which fluid may be returned between core-flow stages.

Abstract: A method for the variation of at least one blade row of a fluid-flow machine, in which, in dependence of the actual operating point, in addition to an aerodynamic speed, at least one further quantity pertinent to the position of the operating point in the family of characteristics of the fluid-flow machine is employed for control.

Abstract: A fluid-flow machine, especially for an aircraft engine, includes a rotor having rotor blades 3. The rotor blades 3 include, on a suction side 9, at least two zones of different surface finish, with one zone being positioned between a rotor blade 3 leading edge 5, a casing line 1, a line SLM and a line EL and being provided with a boundary layer-energizing surface structure, with the line SLM being a meridional flow line at a Mach number-critical blade height of the rotor, and with the line EL being a connecting line of all points E to form a chord-orthogonal projection line EL.

Abstract: A turbomachine blade with a profile skeleton line extending along a meridional flow line, the blade being radially divided into at least three zones (Z0, Z1, Z2) with profile skeleton lines of each zone (Z0, Z1, Z2) provided in each zone from the respective radially inner to the radially outer boundary to satisfy the equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = s P S where P is any point of the profile skeleton line, ?1 is angle of inclination at blade leading edge, ?2 is angle of inclination at blade trailing edge, ?* is dimensionless, specific angle of total curvature, S* is dimensionless; specific extension, ?P is angle of tangent at any point P of profile skeleton line to central meridional flow line, sP is extension of profile skeleton line at any point P, and S is total extension of profile skeleton line.

Abstract: A variable stator of a turbomachine with a profile skeleton line extending along a meridional flow line, with the stator being radially divided into at least three zones (Z0, Z1, Z2) and with the respective radial inner and the radial outer profile skeleton line of each zone (Z0, Z1, Z2) being designed such that it satisfies the following equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = S P S where: P is any point of the profile skeleton line, ?1 is the angle of inclination at the stator leading edge, ?2 is the angle of inclination at the stator trailing edge, ?* is the dimensionless, specific angle of the total curvature, S* is the dimensionless, specific extension, ?P is the angle of the tangent at any point P of the profile skeleton line to the central meridional flow line, sP is the extension of the profile skeleton line at any point P, and S is the total extension of the profile skeleton line.

Abstract: A turbomachine with at least one rotor (6), no or at least one stator (7), and a casing (1), with the rotor (6) comprising several rotor blades (8) attached to a rotating shaft, and with the stator (7) being provided with stationary stator blades (9). The casing (1) is passed by a fluid flowing through rotor (6) and stator (7), and means for the supply of fluid are provided on at least one blade (8, 9) of a blade row of the rotor (6) and/or the stator (7) on aerodynamically critical locations on trailing edge and rim-near surfaces (HRO).

Abstract: A turbomachine having at least one flow path, in which at least one stator blade 2 is arranged, which is variable around a rotational axis 1, and which comprises at its radial end areas one rotary base 3 each, wherein a portion of the rotary base 3 is non-circular, when viewed in a direction of the rotational axis 1 of the stator blade 2.

Abstract: A turbomachine includes at least one rotor (6), at least one stator (7), and a casing (1), with the rotor (6) comprising several rotor blades (8) attached to a rotating shaft, and with the stator (7) being provided with stationary stator blades (9), the casing (1) being passed by a fluid flowing through the rotor (6) and stator (7). Provision is made for the removal of fluid on at least one blade (8, 9) of a blade row of the rotor (6) and/or the stator (7) on non-axially symmetrical, aerodynamically critical locations on blade tip and annulus surfaces (SRO).

Abstract: A turbomachine has at least one rotor blade row designed for extremely high work coefficients (high-load), which—in its center section and/or averaged over the blade height—provides for an essentially swirl-free relative outflow. The respective rotor in its trailing edge area is essentially orientated in meridional direction, with the mean or averaged exit metal angle of the rotor blade ranging from ?10 to +5 degrees.

Abstract: A turbomachine blade is repaired by making a leading edge cutback between two points (A) and (E) where point (A) lies within a range of relative blade height (h/H) of 0?(h/H)point A<0.85, and point (E) lies within a range of 0.95<(h/H)point E?1.0, with (h) being a blade height coordinate which originates at an end of the blade closer to starting point (A), and (H) being the blade height. A cutback trace is defined by (s/SAE) and (c/Cm), with (c) being a local cutback length in meridional flow direction, (Cm) being a meridional chord length, (s) being a local cutback length in radial direction, and (SAE) being a radial cutback length, where (c) gradually increases from point (A) to its maximum at 0.60<s/SAE<0.95, with (c/Cm) there being ?0.25, and then decreasing to ?0.05.

Abstract: A variable stator of a turbomachine with a profile skeleton line extending along a meridional flow line, with the stator being radially divided into at least three zones (Z0, Z1, Z2) and with the respective radial inner and the radial outer profile skeleton line of each zone (Z0, Z1, Z2) being designed such that it satisfies the following equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = S P S where: P is any point of the profile skeleton line, ?1 is the angle of inclination at the stator leading edge, ?2 is the angle of inclination at the stator trailing edge, ?* is the dimensionless, specific angle of the total curvature, S* is the dimensionless, specific extension, ?p is the angle of the tangent at any point P of the profile skeleton line to the central meridional flow line, sp is the extension of the profile skeleton line at any point P, and S is the total extension of the profile skeleton line.

Abstract: A method for the production of secondary fluid ducts for a turbomachine, especially for fluid supply or fluid removal to/from a flow-wetted surface of the turbomachine, with the secondary fluid ducts being produced by an electrochemical machining process.

Abstract: A turbomachine blade with a profile skeleton line extending along a meridional flow line, the blade being radially divided into at least three zones (Z0, Z1, Z2) with profile skeleton lines of each zone (Z0, Z1, Z2) provided in each zone from the respective radially inner to the radially outer boundary to satisfy the equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = s P S where P is any point of the profile skeleton line, ?1 is angle of inclination at blade leading edge, ?2 is angle of inclination at blade trailing edge, ?* is dimensionless, specific angle of total curvature, S* is dimensionless; specific extension, ?P is angle of tangent at any point P of profile skeleton line to central meridional flow line, sP is extension of profile skeleton line at any point P, and S is total extension of profile skeleton line.

Abstract: A blade for an axial-flow turbomachine with a gap-side blade area I which transits into a free blade end and with a hub-side or casing-side blade area II, respectively. The blade 3 forms a flow line profile section with a leading edge VK and a trailing edge HK which establish a forward end point V and a rearward end point H, respectively, by a tangent normal to and intersecting with the profile chord, with the distance between these end points being the profile depth L. The blade 3 includes an enlargement of the profile depth L at a tip of the free blade end which is at least +10 percent and decreases to zero in the blade central section, with the values being non-negative throughout, with the profile enlargement at the trailing edge HK being larger than zero at the tip in the gap-side peripheral section.

Abstract: A fluid-flow machine includes at least one rotor and a free number of stators flown by a fluid, with at least one blade thereof positioned on throat-confining surfaces provided with both a device for fluid removal from the flow path and a device for fluid supply into the flow path (bi-functionality). The machine includes at least one line associated with the device for fluid removal for returning the removed fluid to an upstream position in the flow path and at least one further line associated with the device for fluid supply for supplying the fluid from a further downstream position in the flow path.