Method for determining the remaining service life of a rotor of a thermally loaded turboengine
First Claim
Patent Images
1. A method for determining the remaining service life of a rotor of a thermally loaded turboengine, comprising:
- measuring a temperature on the rotor of the turbine;
deriving a thermal stress on the rotor from the measured temperature; and
using an evaluation unit to calculate the remaining service life of the rotor from the derived thermal stress, wherein the temperature is measured directly at a predetermined point of the rotor, and the thermal stress on the rotor is derived from the measured temperature, wherein the rotor is mounted rotatably about an axis and is surrounded by a casing, rows of moving blades, through which hot working gas flows in an axial direction, are arranged on the rotor one behind the other in the axial direction, the working gas is introduced into the blading of the rotor in an inlet region, and the temperature on the rotor is measured in the inlet region, the inlet region is formed by an inflow spiral, formed in the casing and surrounding the axis annularly, for the radial introduction of the working gas and by a deflection duct, adjoining the inflow spiral, for deflecting the entering working gas from the radial direction to the axial direction, and the temperature on the rotor is measured in the deflection duct shortly before the start of the blading.
2 Assignments
0 Petitions
Accused Products
Abstract
A method for determining the remaining service life of a rotor of a thermally loaded turboengine in which a temperature on the rotor is determined. Thermal stress on the rotor is calculated from the determined temperature, and the remaining service life of the rotor is calculated from the derived thermal stress. The temperature is measured directly at a predetermined point of the rotor, and the thermal stress on the rotor is derived from the measured temperature.
-
Citations
14 Claims
-
1. A method for determining the remaining service life of a rotor of a thermally loaded turboengine, comprising:
-
measuring a temperature on the rotor of the turbine; deriving a thermal stress on the rotor from the measured temperature; and using an evaluation unit to calculate the remaining service life of the rotor from the derived thermal stress, wherein the temperature is measured directly at a predetermined point of the rotor, and the thermal stress on the rotor is derived from the measured temperature, wherein the rotor is mounted rotatably about an axis and is surrounded by a casing, rows of moving blades, through which hot working gas flows in an axial direction, are arranged on the rotor one behind the other in the axial direction, the working gas is introduced into the blading of the rotor in an inlet region, and the temperature on the rotor is measured in the inlet region, the inlet region is formed by an inflow spiral, formed in the casing and surrounding the axis annularly, for the radial introduction of the working gas and by a deflection duct, adjoining the inflow spiral, for deflecting the entering working gas from the radial direction to the axial direction, and the temperature on the rotor is measured in the deflection duct shortly before the start of the blading. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
-
Specification