-
公开(公告)号：US11578655B2
公开(公告)日：2023-02-14
申请号：US16695945
申请日：2019-11-26
Applicant: Rosemount Aerospace Inc.
Inventor： Sathish Thangavel , Andy Holl , Aaron A. Cusher
Abstract: A pressure and temperature probe of a gas turbine engine includes a base portion and an airfoil portion extending from the base portion to an end portion located at a distal end of the probe. The airfoil portion includes a leading edge located at an upstream end of the probe relative to a direction of airflow across the probe. A temperature sensor is located in a temperature sensor chamber located in the airfoil portion, and a temperature airflow hole in the end portion is configured to admit an airflow into the temperature sensor chamber around the temperature sensor. The temperature airflow hole is configured and positioned such that the airflow admitted via the temperature airflow hole has a turning angle of less than 90 degrees into the temperature sensor chamber.
Search Results
1
records
(took 0.007 seconds)
