# US 9,518,850 B2 · Embedded cap probe > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,518,850 B2 - Document ID: US9518850B2 - Status: Granted - Kind: B2 - Application number: 14/015,191 - Filed: 2013-08-30 - Published: 2014-04-03 - Granted: 2016-12-13 - Earliest claimed: 2012-09-28 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Eli Cole Warren - Web page: https://patentgrep.com/patent/US9518850B2 ## CPC - G01B 7/14: for measuring distance or clearance between spaced objects or spaced apertures (G01B7/30 takes precedence) - F01D 11/20: Actively adjusting tip-clearance - F01D 17/06: responsive to speed - F01D 21/003: {Arrangements for testing or measuring (for measuring vibrations G01H)} - G01D 11/30: Supports specially adapted for an instrument; Supports specially adapted for a set of instruments - F05D 2240/11: Shroud seal segments - F05D 2260/97: Reducing windage losses - G01B: MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - G01D: MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The method of claim 1, further comprising the first portion and the second portion of the probe assembly not being assembled to each other before installation within the case. ### Claim 3 (depends on 1) The method of claim 1, further comprising using a seal coating to retain the probe assembly within the case. ### Claim 4 (depends on 1) The method of claim 1, further comprising preparing the bore in the first section of the case, and preparing the inset in the second portion of the case. ### Claim 5 (depends on 4) The method of claim 4, further comprising installing a sleeve and a lead within the bore of the case. ### Claim 6 (depends on 5) The method of claim 5, further comprising installing an outer ceramic pad within the inset of the case. ### Claim 7 (depends on 6) The method of claim 6, further comprising adhering a sensor face to the outer ceramic pad, and adhering an inner ceramic pad to the sensor face and outer ceramic pad. ### Claim 8 (depends on 7) The method of claim 7, further comprising attaching a sensor wire from the lead to the sensor face. ### Claim 9 (depends on 8) The method of claim 8, further comprising applying an abradable coating to the inner ceramic pad, outer ceramic pad, and case to locate and maintain a position of the probe assembly within the case. ### Claim 10 (depends on 9) The method of claim 9, further comprising removing a portion of the abradable coating to accommodate an electrical field of the sensor face. ### Claim 11 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. ### Claim 12 (depends on 11) The case assembly of claim 11, further comprising a coating applied to the second portion and the case to retain the probe assembly within the case. ### Claim 13 (depends on 11) The case assembly of claim 11, wherein the first portion includes a lead assembled to a sleeve, and wherein the sleeve is fixed to the bore. ### Claim 14 (depends on 13) The case assembly of claim 13, wherein the second portion includes an outer ceramic pad fixed to the inset, a sensor face positioned within an inset of the outer ceramic pad, and an inner ceramic pad fixed to the sensor face and the outer ceramic pad. ### Claim 15 (depends on 14) The case assembly of claim 14, wherein the lead includes a sensor wire, the sensor wire attached to the sensor face. ### Claim 16 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. ### Claim 17 (depends on 16) The method of claim 16, further comprising applying the coating to inner surfaces of the probe and the case, the coating composed of abradable material. ### Claim 18 (depends on 17) The method of claim 17, further comprising removing a portion of the coating to accommodate an electric field between a sensor face of the probe and a blade tip. ### Claim 19 (depends on 18) The method of claim 18, further comprising beveling an edge of a remaining portion of the coating.