# US 10,119,423 B2 · Gas turbine engine fan spacer platform attachments > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,119,423 B2 - Document ID: US10119423B2 - Status: Granted - Kind: B2 - Application number: 14/426,252 - Filed: 2013-09-17 - Published: 2015-08-06 - Granted: 2018-11-06 - Earliest claimed: 2012-09-20 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Colin J. Kling; Charles W. Brown; Christopher M. Quinn; Shelton O. Duelm; Peter V. Tomeo; Corey L. Hubbert - Web page: https://patentgrep.com/patent/US10119423B2 ## CPC - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - F01D 11/008: {by spacer elements between the blades, e.g. independent interblade platforms} - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F02C 3/10: with another turbine driving an output shaft but not driving the compressor - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - Y10T 29/4932: Turbomachine making - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub. ## Claims ### Claim 1 A fan hub assembly for a gas turbine engine comprising: a fan hub that includes forward and aft lugs and is configured to rotate about an axis, wherein the forward and aft lugs respectively include an axially extending first and second aperture; a platform; and a first fastener and a second fastener integrally connected with the platform by molding, bonding or threading to the platform, and the first and second fasteners respectively are received in the first and second apertures in a slip fit relationship to secure the platform to the fan hub. ### Claim 2 (depends on 1) The fan hub assembly according to claim 1, wherein the forward lug extends radially inward from the fan hub, and the aft lug extends radially outward from the fan hub. ### Claim 3 (depends on 1) The fan hub assembly according to claim 1, comprising a spinner secured to the fan hub to axially retain the platform against the forward lug. ### Claim 4 (depends on 1) The fan hub assembly according to claim 1, wherein each of the first and second fasteners is a pin. ### Claim 5 (depends on 4) The fan hub assembly according to claim 4, wherein each of the pins is integral within the platform. ### Claim 6 (depends on 4) The fan hub assembly according to claim 4, wherein each of the pins extends aftward from the platform. ### Claim 7 (depends on 4) The fan hub assembly according to claim 4, wherein the pin is bonded to the platform. ### Claim 8 (depends on 1) The fan hub assembly according to claim 1, comprising fan blades secured to the fan hub, the platform secured circumferentially between adjacent fan blades. ### Claim 9 A fan hub assembly for a gas turbine engine comprising: a fan hub configured to rotate about an axis and including a radially extending aperture; a fan blade secured to the fan hub; a platform that is separate and discrete from the fan blade and provides an inner flow surface that has a first hole and an axially extending flange is formed integrally with the platform providing an unbroken, unitary structure therewith, the axially extending flange includes a second hole; and a fastener that is a bolt aligned with the first hole and the fastener extends through the second hole, the fastener threadingly received in the aperture to secure the platform to the fan hub. ### Claim 10 (depends on 9) The fan hub assembly according to claim 9, wherein the fan hub includes an axially extending aperture receiving a second fastener securing the platform to the fan hub. ### Claim 11 (depends on 10) The fan hub assembly according to claim 10, wherein the second fastener is threaded to the platform and in a slip fit relationship with respect to the axially extending aperture.