Embedded cap probe
AssigneeUnited Technologies Corporation
InventorEli Cole Warren
Life of this patent
Estimating the term…
Abstract
A method for installing a probe assembly in a case of a gas turbine engine is disclosed. The method may include installing a first portion of the probe assembly within a first section of the case, and installing a second portion of the probe assembly within a second section of the case. A case assembly within a gas turbine engine is also disclosed. The case assembly may include a case in at least one of a compressor and a turbine, and a probe assembly. The probe assembly may include a first portion positioned within a bore of the case, and a second portion positioned within an inset of the case, the bore having a smaller diameter than the inset.
Claims19
A method for installing a probe assembly in a case of a gas turbine engine, comprising:
- installing a first portion of the probe assembly within a bore of a first section of the case;
- and
- separately installing a second portion of the probe assembly within an inset of a second section of the case, the inset positioned on an inner diameter surface of the case circumscribing and facing a blade array of the gas turbine engine, the bore having a smaller diameter than the inset and extending into the case and from the inset to an outer diameter surface of the case, wherein the second portion is larger than the bore.
A case assembly within a gas turbine engine, comprising:
- a case in at least one of a compressor and a turbine;
- and
- a probe assembly including
- a first portion positioned within a bore of the case, and
- a second portion positioned within an inset on an inner diameter surface of the case circumscribing and facing a blade array of the at least one of the compressor and the turbine, the bore having a smaller diameter than the inset and extending from the inset into the case and to an outer diameter surface of the case, wherein the second portion is larger than the bore.
A method for retaining a probe within a case of a gas turbine engine, the probe having a first portion and a second portion, the first portion being located within a bore extending through the case and the second portion being located in an inset located on an inner diameter surface of the case, the inset facing a blade array of the gas turbine engine, wherein the bore extends from the inset into the case and to an outer diameter surface of the case and has a smaller periphery than that of the inset, the method comprising the steps of:
- inserting the first portion into the bore of the case;
- inserting the second portion into the inset;
- applying a coating to the second portion to retain the probe within the case, wherein the second portion is larger than the bore.
Dependencies are inferred from the claim text.