# US 2018/0320708 A1 · Pin to reduce relative rotational movement of disk and spacer of turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0320708 A1 - Document ID: US20180320708A1 - Status: Published application - Kind: A1 - Application number: 15/588,871 - Filed: 2017-05-08 - Published: 2018-11-08 - Earliest claimed: 2017-05-08 - Assignees: Solar Turbines Incorporated - Applicants: Solar Turbines Incorporated - Inventors: Kenneth Gregory Thomas - Web page: https://patentgrep.com/patent/US20180320708A1 ## CPC - F04D 29/644: {especially adapted for elastic fluid pumps} - F01D 5/066: {Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps} - F04D 19/02: Multi-stage pumps - F04D 29/321: {for axial flow compressors} - F05D 2250/13: trapezoidal - F05D 2250/132: hexagonal - F05D 2260/36: by a form fit connection, e.g. by interlocking - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract An axial compressor of a turbine engine includes a plurality of disk and spacer pairs oriented along a common axis of rotation. Each of a disk and a spacer of the disk and spacer pairs has a contacting face defining an engagement between the disk and the spacer. The contacting face of each of the disk and the spacer includes a recessed area. A pin has a stem received within the recessed area of the disk and a head received within the recessed area of the spacer. The head of the pin includes at least two flats corresponding to complementary surfaces of the recessed area of the spacer. ## Claims ### Claim 1 An axial compressor of a turbine engine, including: a plurality of disk and spacer pairs oriented along a common axis of rotation, each of a disk and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer; the contacting face of each of the disk and the spacer including a recessed area; and a pin having a stem received within the recessed area of the disk and a head received within the recessed area of the spacer; the head of the pin including at least two flats corresponding to complementary surfaces of the recessed area of the spacer. ### Claim 2 (depends on 1) The axial compressor of claim 1, wherein the disk and the spacer have a thermal interference engagement. ### Claim 3 (depends on 1) The axial compressor of claim 1, wherein the head of the pin has a hexagonal shape. ### Claim 4 (depends on 3) The axial compressor of claim 3, wherein the recessed area of the spacer has a shape corresponding to the hexagonal shape of the head of the pin. ### Claim 5 (depends on 3) The axial compressor of claim 3, wherein the stem of the pin has a cylindrical shape. ### Claim 6 (depends on 5) The axial compressor of claim 5, wherein the recessed area of the disk has a shape corresponding to the cylindrical shape of the stem of the pin. ### Claim 7 (depends on 3) The axial compressor of claim 3, wherein the pin has a passage therethrough oriented along a longitudinal axis of the pin. ### Claim 8 (depends on 1) The axial compressor of claim 1, further including a plurality of recessed areas spaced about each of the disk and the spacer, and four pins configured for receipt within the plurality of recessed areas. ### Claim 9 (depends on 1) The axial compressor of claim 1, further including a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer. ### Claim 10 A method of operating a turbine engine, including steps of: rotating a disk and spacer pair of a plurality of disk and spacer pairs about a common axis of rotation; engaging a contacting face of a disk of the disk and spacer pairs with a contacting face of a spacer of the disk and spacer pairs during rotation; and restricting relative rotation of the disk and the spacer using a pin having a stem received within a recessed area of the disk and a head received within a recessed area of the spacer; wherein the restricting step includes contacting at least two flats of the head of the pin with complementary surfaces of the recessed area of the spacer. ### Claim 11 (depends on 10) The method of claim 10, further including forming a thermal interference engagement of the disk and the spacer during operation of the turbine engine. ### Claim 12 (depends on 11) The method of claim 11, further including performing a hot shutdown of the turbine engine, and reducing a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer. ### Claim 13 (depends on 10) The method of claim 10, further including engaging a hexagonally shaped head of the pin with the complementary surfaces of the recessed area of the spacer. ### Claim 14 (depends on 10) The method of claim 10, wherein the restricting step includes engaging four pins with four recessed areas spaced about each of the disk and the spacer. ### Claim 15 A turbine engine, including: an axial compressor, including: a plurality of disk and spacer pairs oriented along a common axis of rotation, each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer, the contacting face of each of the disk and the spacer including a recessed area; and a pin having a stem received within the recessed area of the disk and a hexagonally shaped head received within the recessed area of the spacer. ### Claim 16 (depends on 15) The turbine engine of claim 15, wherein the pin has a passage therethrough oriented along a longitudinal axis of the pin. ### Claim 17 (depends on 15) The turbine engine of claim 15, wherein the stem of the pin has a cylindrical shape. ### Claim 18 (depends on 15) The turbine engine of claim 15, wherein the disk and the spacer have a thermal interference engagement. ### Claim 19 (depends on 15) The turbine engine of claim 15, further including a predetermined clearance between a top surface of the head of the pin and an inner surface of the recessed area of the spacer. ### Claim 20 (depends on 15) The turbine engine of claim 15, further including a plurality of recessed areas spaced about each of the disk and the spacer, and four pins configured for receipt within the plurality of recessed areas.