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 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: An aircraft propulsion unit includes a gas-turbine core engine 10 having at least one compressor, one combustion chamber and one turbine driving a main shaft 11. The main shaft 11 of the gas-turbine core engine 10 is operationally connected to at least two separate fans 6-9 via a mechanical drive connection, each of them being arranged beside the gas-turbine core engine 10.

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 main flow path 2 which is confined by a hub 3 and a casing 1 and in which at least one row of blades 5 is arranged. A gap 11 is provided on at least one blade row 5 between a blade end and a main flow path confinement, with the blade end and the main flow path confinement performing a rotary movement relative to each other. At least one reversing duct 7 is provided in the area of the blade leading edge in the main flow path confinement at a discrete circumferential position. The reversing duct 7 connects two openings 12, 13 arranged on the main flow path confinement.

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. Blade 3 forms a flow line profile section with leading edge VK and trailing edge HK which establish forward end point V and rearward end point H, respectively, by a tangent normal to and intersecting with the profile chord, with the distance between these end points being profile depth L. Blade 3 includes an enlargement of 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 trailing edge HK being larger than zero at the tip in the gap-side peripheral section.

Abstract: A turbomachine includes at least one rotor 1 featuring a hub and one stator 2, with a casing 5 confining the flow through the rotor 1 and the stator 2 to the outside. It also includes running-gap adjacent hub and casing surfaces LNGO, with openings being provided along the circumference on at least one running-gap adjacent hub and casing surface LNGO which form at least one dynamically operating supply point DAV which is connected via a least one line 6 to at least one opening on a blade-passage confining surface SKO.

Abstract: A fluid-flow machine has at least one row of blades 5 having blade ends moving relative to one of a hub 3 and a casing 1, with a gap 11 positioned therebetween. At least one groove 7 extends essentially in a circumferential direction of the machine is in an area of the gap 11 along at least part of the circumference, with the extension of the groove 7 in the circumferential direction being large as compared to the extension of the groove 7 in the meridional flow direction. A cross-sectional area of the groove 7, in meridional view of the fluid-flow machine, essentially departs from a parallelogrammic shape and, due to its contour, is inclined in an upstream direction. A centroid of the groove cross-sectional area is provided upstream of the center of the groove aperture 12 on the main flow path.

Abstract: A fluid flow machine includes at least one rotor blade row designed for high work coefficients, 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, which essentially corresponds to the meridional flow direction.

Abstract: A fluid flow machine includes a main flow path in which at least one row of blades (3, 4) is arranged, and a blade shroud (2) which forms a confinement of the main flow path in the area of a blade row (3, 4) and is arranged in a recessed cavity (10) of a surrounding physical structure (11). The cavity (10) so formed between the shroud (2) and the surrounding physical structure (11) is provided with an annular connection (14) to the main flow path at least on the outflow side of the blade shroud (2), and with the blade shroud (2) being penetrated by at least one secondary flow path (16) which, commencing at a location of high pressure on the shroud (2), issues at a surface wetted by the main flow.

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 for use in a fluid-flow machine, where at least one of the meridional flow line profile sections MSLi and MSLo is provided at a distance of max. 35% of the main flow path width from the respective inner and outer main flow path boundaries. The blade has in at least parts of a central area a multi-profile configuration such that at least two partial profiles (7, 9, 10) arranged one behind the other in the flow direction are provided, of which each has substantially the shape of a blade profile, where a passage (8) is provided between each two partial profiles and is passed through by fluid from the blade pressure side to the blade suction side.

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 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 flow duct confined by a wall of a casing, with a fluid supply chamber being arranged in an area of the wall, which is in flow connection with an injector insert. The injector insert is provided with an injector nozzle for supplying fluid from the fluid supply chamber into the flow duct. The injector insert is closely connected to the wall of the fluid supply chamber.

Abstract: A fluid flow machine includes an annulus duct formed between a casing and a rotor drum, which is rotatable about a machine axis. At least one row of rotor blades is arranged in the annulus duct, with the latter forming a main flow path and with at least one fluid injector nozzle being arranged in the area of a wall of the casing and/or of the rotor drum. At least part of the injector nozzle protrudes into the main flow path and is provided for the generation of a jet which is tangentially directed to the wall of the main flow path.

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 fluid flow machine includes at least one casing 1 and at least one rotor drum 3 rotatable about a machine axis 4, with stator vanes 8 and rotor blades 7 being arranged in an annulus duct 2 formed between the casing 1 and the rotor drum 3 The annulus duct 2 is divided into an outer annular duct 5 and an inner annular duct 6 by at least one annular flow divider 11, in each of which rotor blades 7 and stator vanes 8 are arranged Outer rotor blades 7a, which are arranged in the outer annular duct 5, are rotatable at a different speed than the inner rotor blades 7b, which are arranged in the inner annular duct 6.

Abstract: A fluid flow machine has a flow path (2) which is confined by at least one wall, on which at least one row of blades (6, 7) is fixedly mounted. At least one fluid offtake opening (9) and at least one fluid supply opening (10), which are connected by at least one fluid return path (11), are arranged in the wall in an area of a blade row (6, 7), with a circumferential extension of the fluid supply opening (10) being less than a distance between two adjacent blades.

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.