| 摘要 |
The invention relates to a high temperature pressure sensor element (10; 20), in particular for jet engines, comprising a substrate (11) with an inner region (12) configured therein, a defomable membrane (13) which separates the inner region (12) from the outer region and deforms during operation in the event of a change of pressure, and a strain gauge element (14a, 14b, 14c) disposed on the membrane (13) for measuring the deformation of said membrane (13). The substrate (11), the membrane (13) and the strain gauge element (14a, 14b, 14c) are all made of the same high temperature stable material, particularly an alloy, such as a nickel-based alloy. A component for a jet engine, such as for example a turbine blade for an aircraft or a rocket engine, comprises such an integrated high temperature pressure sensor element (10; 20). ® KIPO & WIPO 2009 |
