High-temperature forging, particularly of titanium aluminides
a technology of titanium aluminide and high-temperature forging, which is applied in the direction of furnaces, furnace types, mechanical equipment, etc., can solve the problems of difficult processing of tial alloys, risk of differing the volume of forging blanks, and the method having the preceding swage shaping is also complex
Inactive Publication Date: 2019-01-17
MTU AERO ENGINES GMBH
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Benefits of technology
The present invention provides a method for forging components at high temperatures, which can be done using a small expenditure. This method can be used to reshape forging blanks or preforms of titanium-aluminum (TiAl) materials for making components of turbomachines like gas turbines and aircraft engines. The invention provides an efficient way to forge components of this material.
Problems solved by technology
Of course, TiAl alloys are not easy to process and the structure of TiAl materials must be established exactly in order to obtain the desired mechanical properties.
Of course, the method having the preceding swage shaping is also complicated, and additionally, based on the temperature difference between the forging blank and the die, due to the possibly intense cooling of the forging blank thereby in the forging die, there is the danger of a shaping that differs over the volume of the forging blank.
Method used
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Experimental program
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Embodiment Construction
[0009]The invention proposes to carry out a quasi-isothermal forging instead of an isothermal forging when components are forged at high temperatures, so that the expenditure for providing and operating a high-temperature forging die can be reduced. For this purpose, it is provided according to the invention that the forging die, in which the forging reshaping will occur, is preheated to a first temperature, which is lower than a second temperature at which the preform, which will be reshaped by forging, is heated prior to the forging. In this case, the two temperatures are selected so that in the case of the corresponding forging process, the surface temperature of the preform to be forged during the forging process does not decrease to below a minimum forging temperature, and, at the same time, the die temperature of the forging die does not increase to above a maximum die temperature. In this way, it can be achieved that in the case of a given forging die, higher forging temperat...
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Abstract
The present invention relates to a method for forging a component, in particular a component made of a TiAl material, in which the die for forging is heated to a specified first temperature prior to the forging, and in which a preform of the component to be forged is preheated to a specified second temperature, wherein the first temperature is lower than the second temperature, and first and second temperatures are selected so that during the forging, the surface temperature of the preform does not fall below a minimum forging temperature, and the temperature of the die does not increase above a maximum die temperature.
Description
BACKGROUND OF THE INVENTION[0001]The present invention relates to a method for manufacturing forged components, particularly components made of a TiAl alloy, and preferably components for gas turbines, preferably aircraft engines, and, in particular, turbine blades or vanes for low-pressure turbines.[0002]Components made of titanium aluminides or TiAl alloys are of interest for application in gas turbines, in particular aircraft engines, due to their small specific weight or low density and their mechanical properties.[0003]Titanium aluminides or TiAl alloys are understood here to be alloys that comprise titanium and aluminum as the principal constituents, so that the chemical composition thereof contains aluminum and titanium as constituents with the highest percentages. Moreover, TiAl alloys are characterized by the formation of intermetallic phases, such as γ—TiAl or α2—Ti3Al, which bestow good strength properties on the material.[0004]Of course, TiAl alloys are not easy to proce...
Claims
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Patent Timeline
Login to View More IPC IPC(8): C22F1/18B21J5/02B21J17/00C22C14/00
CPCC22F1/183C22C14/00B21J17/00B21J5/02B21J1/06B21K3/04
InventorSCHLOFFER, MARTIN
OwnerMTU AERO ENGINES GMBH