# US 10,480,530 B2 · Fan Containment case for gas turbine engines > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,530 B2 - Document ID: US10480530B2 - Status: Granted - Kind: B2 - Application number: 15/686,255 - Filed: 2017-08-25 - Published: 2019-02-28 - Granted: 2019-11-19 - Earliest claimed: 2017-08-25 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Mark W. Costa - Web page: https://patentgrep.com/patent/US10480530B2 ## CPC - F04D 29/526: {Details of the casing section radially opposing blade tips (ducts F04D29/545)} - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F01D 21/045: {special arrangements in stators or in rotors dealing with breaking-off of part of rotor} - F02K 3/06: with front fan - F04D 29/023: {especially adapted for elastic fluid pumps} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2230/60: Assembly methods - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2240/15: Heat shield - F05D 2240/20: Rotors - F05D 2250/283: honeycomb - F05D 2300/603: Composites; e.g. fibre-reinforced - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness. ## Claims ### Claim 1 A fan section for a gas turbine engine comprising: a fan containment case assembly including: an outer case extending about an axis; a thermally conforming liner assembly radially inward of the outer case, the liner assembly including a shell; a wrap radially outward of the shell; and a ballistic liner between the outer case and the wrap; wherein the wrap has a first fiber construction, the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness, the wrap directly contacts an outer diameter of the shell, and the first fiber construction of the wrap is made of substantially non-impregnated fibers. ### Claim 2 (depends on 1) The fan section as recited in claim 1, wherein the second fiber construction of the ballistic liner is made of resin impregnated fibers. ### Claim 3 (depends on 2) The fan section as recited in claim 2, wherein the fibers of the first fiber construction are aramid fibers. ### Claim 4 (depends on 3) The fan section as recited in claim 3, wherein the outer case is made of a composite material. ### Claim 5 (depends on 1) The fan section as recited in claim 1, comprising a plurality of fan blades rotatable about the axis within a fan blade region of the fan containment case assembly. ### Claim 6 (depends on 5) The fan section as recited in claim 5, wherein each of the ballistic liner and the wrap circumferentially surrounds the plurality of fan blades. ### Claim 7 (depends on 5) The fan section as recited in claim 5, wherein: the shell includes a first section, a second section located aft of the first section, and a third section located aft of the second section; and the thermally conforming liner assembly includes a forward acoustic liner radially inward of the first section of the shell, an abradable rub layer defining a clearance gap with the plurality of fan blades, and a honeycomb core between the second section of the shell and the abradable rub layer. ### Claim 8 (depends on 6) The fan section as recited in claim 6, comprising a plurality of ribs circumferentially distributed about the outer diameter of the shell, and a plurality of torque blocks mechanically attached to the outer case, wherein at least one torque block of the plurality of torque blocks being positioned between at least one pair of the plurality of ribs to oppose rotation of the shell relative to the outer case. ### Claim 9 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an engine longitudinal axis; a compressor section; a turbine section driving the fan; and a fan containment case assembly comprising: an outer case extending about the engine longitudinal axis; a thermally conforming liner assembly radially inward of the outer case, the liner assembly including a shell; a wrap between the outer case and the shell, at least partially surrounding the plurality of fan blades, and made of substantially non-impregnated fibers; and a ballistic liner between the outer case and the wrap. ### Claim 10 (depends on 9) The gas turbine engine as recited in claim 9, wherein the ballistic liner comprises a metal material. ### Claim 11 (depends on 9) The gas turbine engine as recited in claim 9, wherein the ballistic liner is made of resin impregnated fibers, the wrap is bonded to an outer diameter of the shell, and the ballistic liner is bonded to the outer case. ### Claim 12 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an engine longitudinal axis; a compressor section; a turbine section driving the fan; and a fan containment case assembly comprising: an outer case extending about the engine longitudinal axis; a thermally conforming liner assembly radially inward of the outer case, the liner assembly including a shell; a wrap between the outer case and the shell, at least partially surrounding the plurality of fan blades, and made of substantially non-impregnated fibers; and wherein the outer case is made of a composite material. ### Claim 13 A method of assembling a fan containment case comprising: attaching a ballistic liner to an inner diameter of an outer case; preparing a thermally conforming liner assembly, including attaching a wrap to an outer diameter of a shell, the wrap made of substantially non-impregnated fibers; and positioning the thermally conforming liner assembly radially inward of the ballistic liner. ### Claim 14 (depends on 13) The method as recited in claim 13, comprising positioning the thermally conforming liner assembly to at least partially surround a plurality of fan blades. ### Claim 15 (depends on 14) The method as recited in claim 14, wherein the step of preparing includes attaching an acoustic liner to an inner diameter of the shell, attaching a honeycomb core to an inner diameter of the shell, and attaching an abradable rub layer to an inner diameter of the honeycomb core, the abradable rub layer defining a gas flowpath surface adjacent to a plurality of fan blades. ### Claim 16 (depends on 13) The method as recited in claim 13, wherein the ballistic liner is made of resin impregnated fibers. ### Claim 17 (depends on 13) The method as recited in claim 13, wherein the step of preparing includes attaching a plurality of ribs to the shell, and the step of positioning includes axially aligning the plurality of ribs between a plurality of torque blocks of the outer case to oppose rotation of the thermally conforming liner assembly relative to the outer case. ### Claim 18 (depends on 1) The fan section as recited in claim 1, wherein the outer case is made of a composite material. ### Claim 19 (depends on 9) The gas turbine engine as recited in claim 9, wherein the outer case is made of a composite material. ### Claim 20 (depends on 13) The method as recited in claim 13, wherein the outer case is made of a composite material.