Abstract: A protective ring (7) for a fan casing (2) of a gas-turbine engine equipped with a fan having especially metallic fan blades (3) includes a one-piece fiber-composite ring (8) with a ceramic cover (9) arranged on the ring inner surface facing the fan blades, and preferably formed by individual panels embedded in a ductile material, this cover (9)—upon the impingement of broken-off blade fragments—forms a crack network corresponding to an arrangement of the sintered starting ceramic particles and subsequently disintegrates into small particles, thereby absorbing a great part of the kinetic energy caused by the impinging blade fragment. Consequential damage to the protective ring is thereby minimized.

Abstract: A titanium sheet to be formed is heated in a sealingly closed tool by the radiation heat from the heating elements integrated into the tool to a forming temperature not exceeding 600° C., and is deformed towards a cold tool contour by the action of a non-oxidizing gaseous pressure medium introduced into the tool and heated to the hot-forming temperature, as well as by underpressure generated on the side of the workpiece facing away from the pressure medium.

Abstract: A gas-turbine engine fan blade made of a textile composite material includes short carbon fiber intermediate layers (8) for forming the blade root arranged between splayed carbon fiber layers (7) in the blade root (2). In a compressive stress-affected zone (11) of the blade root, the fiber layers extend parallel to the flanks (12) of the blade root. The diversion of the carbon fiber layers (7) up to the splayed area is effected in a transition area (13). A glass fiber outer layer (10) arranged on the flanks (12) of the blade root gradually runs out at a transition zone (15) of the transition area (13), this zone being diverted at a certain radius. Between the glass fiber outer layer and the outer carbon fiber layer there is a carbon fiber layer (9) oriented at +/?45°.

Abstract: With a hybrid fan blade, the supporting structure (1) in fiber-composite material is enclosed by an enveloping structure (2) only in an area of the airfoil, with a suction-side sheet-metal cover of the enveloping structure being pre-stressed in tension and a pressure-side sheet-metal cover of the enveloping structure being pre-stressed in compression. This reduces the hazard of delamination between the enveloping structure and the supporting structure.

Abstract: A fan blade for a gas-turbine engine which comprises a supporting structure (2) in fiber-composite material is enclosed by a sheet-metal enveloping structure (4) only in an area of the airfoil (3) such that the loads and stresses acting on the blade root (11), as well as the risk of delamination caused by the high bending load in the transition area between airfoil and blade root, are minimized.

Abstract: With a method for the manufacture of fiber-composite components, more particularly of fan blades for aircraft engines, dry fiber mats are superimposed in a lay-up mold, correctly positioned and fixed with locating pins and subsequently sewn in the mold. Metallic indicators are provided on at least one mat. The preformed entity of fiber mats is whipped at its edges with thermoplastic material and subsequently smoothed by application of heat. Remaining fiber residues are cut off. The blank thus available is infiltrated with synthetic resin in an infiltration mold or a sheathing remaining on the component. The fiber mats are checked for correct positioning by non-destructive inspection procedures. The fiber-composite component thus formed conforms to high quality requirements.

Abstract: On an intake cone made of fiber compound material for a gas turbine engine, the conical part, the attachment part and the fairing part are manufactured as one piece from a plurality of mutually crossing and covering winding layers (1) forming an interlace (2). The winding layers include parallel, alternately adjacent glass fiber strands and carbon fiber strands of equal thickness. The one-piece intake cone is producible and mountable cost-effectively and is characterized by elasticity, stiffness and impact resistance.

Abstract: An axial-flow compressor for a gas turbine engine has a rotor drum (2) in thermally lower loaded first compressor stages (3 to 6) which includes a one-piece ring, or rotor rings (7 to 10) attached to one another. Fiber belts (18, 21) are wound onto these rings close to the rotor blades and include carbon fibers embedded in a high-temperature resistant polymer matrix. As the rotor disks can be dispensed with, since their function will be assumed by the fiber belts, the compressor features low weight, requires limited space only, and, in addition, can be produced cost-effectively.

Abstract: A hollow fan blade for the fan of an aircraft engine includes a blade base section (2) and a blade tip section (5) which are assembled at opposing faying surfaces (6, 6?) by a joining process. Starting from the respective faying surface, cavities (7, 9) are produced in the two blade portions (2, 5) which are dimensioned in accordance with the loads occurring in the respective blade areas. The joining weld (4) is in a low-loaded area. The blade base section and the blade tip section can be constructed of solid material with formed-in cavities. The blade tip section can also be a sheet-metal structure.

Abstract: This invention relates to a method for the manufacture of a gas-turbine combustion chamber which consists of individual wall sections produced by casting. To make up the combustion chamber, the wall sections are joined by laser welding. Preferably, the individual wall sections are segments of the annular or circular combustion chamber, with the casting material of the wall sections being a high-temperature nickel-base casting alloy.

Abstract: In a supersonic area, on a leading edge (2) of a compressor blade (1) for a gas turbine engine, a replaceable, longitudinally elastically deformable leading edge rail (7) with slender tip (11) and limited weight is positively held in a locating groove (3) and at a stop (6) and elastically locked by the curved blade form. While the maintenance effort is reduced, safe operation and long service life of the compressor (fan) are ensured.

Abstract: On a fixture for electro-chemical machining for the production of long, curved cavities (11) in a component (12), the working electrode (3) of the electro-chemical machining tool (1) is connected to a guide body (1a) which moveably rests against the inner walls of the respective cavity by means of power-actuated guide elements (2), with the guide body being connected to a flexurally soft and torsionally stiff guide linkage (5) coupled to a feed and rotary drive. Control of the movement of the guide body is accomplished in dependence of at least one wall thickness measured with a measuring device (13, 14) during feed movement.

Abstract: An inexpensively manufacturable arrangement for the cooling of thermally highly loaded components, for example the combustion chamber of a gas turbine, comprises cavities (4) provided on the thermally loaded inner surface/air exit side (3) of the wall (1) of the component which are supplied with a cooling medium from the outer surface/air inlet side (5) via cooling air openings (6) and which are covered by a heat resistant wire mesh (7) of a certain permeability. The cavity, which acts as pressure accumulator, forms, in connection with the wire mesh, a uniform pressurized-air film (8) for the cooling and heat shielding of the wall surface.

Abstract: A compressor blade for an aircraft engine includes a blade core made of a fiber compound material and a metallic enclosing structure. The enclosing structure is of a multi-part design and includes blanks (4, 5) attached to the blade core by a metallic weave (6) on the suction side and on the pressure side, with the two blanks being firmly connected at the aerodynamically shaped leading edge of the compressor blade by to a leading-edge former (3). Depending on the specific loads applied on the pressure side and on the suction side, welds attaching the blanks to the leading-edge former (8, 9) are offset relative to each other and the material thicknesses of the components of the enveloping structure are matched to each other.

Abstract: A protective ring (4) for the fan blades (2, 3) of a gas turbine engine includes a material combination of metal bands and polymer-bonded fiber-weave layers interconnected in alternating arrangement. The protective ring thus formed, which is characterized by tough-elastic properties and low weight, can be used as a full containment (4?) with sufficiently large wall thickness or as a penetration containment (4?) with smaller wall thickness and with a trapping layer arranged on the outer circumference. As a full containment, the protective ring has impact-absorption capacity, as a penetration containment it prevents a further destruction of the broken-through protective ring.

Abstract: For material reduction, a fan blade made of solid material for a gas-turbine engine is provided in the area of the blade tip with at least one cavity (5) extending from the face of the blade tip. Thus, apart from the aspect of weight saving, the vibration amplitudes and the centrifugal forces can be reduced considerably and the natural vibration behavior improved in a simple manner, ultimately increasing mechanical strength.

Abstract: The invention relates to a method for producing components with a high load capacity from ?+? TiAl alloys, especially for producing components for aircraft engines or stationary gas turbines. According to this method, enclosed TiAl blanks of globular structure are preformed by isothermal primary forming in the ?+?? or ? phase area. The preforms are then shaped out into components with a predeterminable contour by means of at least one isothermal secondary forming process, with dynamic recrystallization in the ?+?? or ? phase area. The microstructure is adjusted by solution annealing the components in the ? phase area and then cooling them off rapidly.

Abstract: An inexpensively manufacturable arrangement for the cooling of thermally highly loaded components, for example the combustion chamber of a gas turbine, comprises cavities (4) provided on the thermally loaded inner surface/air exit side (3) of the wall (1) of the component which are supplied with a cooling medium from the outer surface/air inlet side (5) via cooling air openings (6) and which are covered by a heat resistant wire mesh (7) of a certain permeability. The cavity, which acts as pressure accumulator, forms, in connection with the wire mesh, a uniform pressurized-air film (8) for the cooling and heat shielding of the wall surface.

Abstract: On a compressor blade (1) for gas turbine engines which is made of a fiber-composite core (4) with metallic enclosure (5) and which comprises a blade root (3) connected to an airfoil (2) and held in a recess (9) of a compressor disk (10), the fiber-composite core is made of transversely compressed fibers with subsequent matrix infiltration and is intimately connected via a surface enlargement by a micro-structure (7) to inner surfaces of the enclosure (5). Thus, the forces are introduced into the blade root (3) directly via the fiber material. Opposite side faces of the longitudinally straight blade root (3) each feature circularly arched bearing faces (8) with different centers (M1, M2) which mate with similarly arched bearing areas (11) provided in the recess (9) to provide for a limited, dampened pendular movement for the absorption of the bending forces acting upon the fiber-composite core.

Abstract: A hollow fan blade for the fan of an aircraft engine includes a blade base section (2) and a blade tip section (5) which are assembled at opposing faying surfaces (6, 6?) by a joining process. Starting from the respective faying surface, cavities (7, 9) are produced in the two blade portions (2, 5) which are dimensioned in accordance with the loads occurring in the respective blade areas. The joining weld (4) is in a low-loaded area. The blade base section and the blade tip section can be constructed of solid material with formed-in cavities. The blade tip section can also be a sheet-metal structure.