# US 9,435,293 B2 · Full ring sliding nacelle with thrust reverser > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,435,293 B2 - Document ID: US9435293B2 - Status: Granted - Kind: B2 - Application number: 14/187,027 - Filed: 2014-02-21 - Published: 2015-05-07 - Granted: 2016-09-06 - Earliest claimed: 2013-02-22 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Gabriel L. Suciu; Jesse M. Chandler; T. David Bomzer - Web page: https://patentgrep.com/patent/US9435293B2 ## CPC - F02K 1/605: {the aft end of the engine cowling being movable to uncover openings for the reversed flow} - 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 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02K 1/60: by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers - F02K 1/62: by blocking the rearward discharge by means of flaps - F02K 1/625: {the aft end of the engine cowling being movable to uncover openings for the reversed flow} - F02K 1/64: Reversing fan flow - F02K 1/70: using thrust reverser flaps or doors mounted on the fan housing - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - F02K 1/763: {with actuating systems or actuating devices; Arrangement of actuators for thrust reversers} - F02K 1/766: {with blocking systems or locking devices; Arrangement of locking devices for thrust reversers} - F05D 2220/32: in gas turbines - F05D 2230/72: Maintenance - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2270/051: Thrust - 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) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion. ## Claims ### Claim 1 A gas turbine engine comprising: a fore pylon; a first annular portion that is stationary and adapted for partially surrounding an engine core, the first annular portion including a fore pylon connecting portion; a rail coupled to the fore pylon and extending in an aft direction from the first annular portion; a second annular portion, aft of the first annular portion and coupled to the rail, the second annular portion being movable along an engine core centerline between a closed position and at least one open position, wherein the second annular portion is configured to engage the first annular portion in the closed position, thereby preventing access to the engine core; and a thrust reverser arranged in the second annular portion, wherein the thrust reverser is a pivot thrust reverser comprising: a first tandem pivot door subassembly comprising a first inner panel and a first outer panel, wherein the first inner panel and the first outer panel are connected by a first sliding rail that extends from one of the first inner panel and the first outer panel and is in contact with the other one of the first inner panel and the first outer panel, such that the first inner panel slides along the first outer panel when the first tandem pivot door subassembly is being deployed and stowed; and a second tandem pivot door subassembly comprising a second inner panel and a second outer panel, wherein the second inner panel and the second outer panel are connected by a second sliding rail that extends from one of the second inner panel and the second outer panel and is in contact with the other one of the second inner panel and the second outer panel, such that the second inner panel slides along the second outer panel when the second tandem pivot door subassembly is being deployed and stowed; wherein each of the first tandem pivot door subassembly and the second tandem pivot door subassembly respectively surround substantially half of the engine core when deployed. ### Claim 2 A gas turbine engine comprising: a fore pylon; a first annular portion that is stationary and adapted for partially surrounding an engine core, the first annular portion including a fore pylon connecting portion; a rail coupled to the fore pylon and extending in an aft direction from the first annular portion; a second annular portion, aft of the first annular portion and coupled to the rail, the second annular portion being movable along an engine core centerline between a closed position and at least one open position, wherein the second annular portion is configured to engage the first annular portion in the closed position, thereby preventing access to the engine core; and a thrust reverser arranged in the second annular portion, wherein the thrust reverser is a pivot thrust reverser comprising: a first tandem pivot door subassembly; a second tandem pivot door subassembly; an actuator connected to the second annular portion, the actuator being oriented parallel to the engine core centerline; a first linkage of the first tandem pivot door subassembly; and a second linkage of the second tandem pivot door subassembly; wherein each of the first linkage and the second linkage are connected to the actuator which pivots the first tandem pivot door subassembly and the second tandem pivot door subassembly on respective pivot axes that are positionally fixed with respect to the second annular portion; wherein the first tandem pivot door subassembly comprises a first inner panel and a first outer panel, wherein the first inner panel and the first outer panel are connected by a first sliding rail that extends from one of the first inner panel and the first outer panel and is in contact with the other one of the first inner panel and the first outer panel, such that the first inner panel slides along the first outer panel when the first tandem pivot door subassembly is being deployed and stowed; wherein the second tandem pivot door subassembly comprises a second inner panel and a second outer panel, wherein the second inner panel and the second outer panel are connected by a second sliding rail that extends from one of the second inner panel and the second outer panel and is in contact with the other one of the second inner panel and the second outer panel, such that the second inner panel slides along the second outer panel when the second tandem pivot door subassembly is being deployed and stowed; and wherein each of the first tandem pivot door subassembly and the second tandem pivot door subassembly respectively surround substantially half of the engine core when deployed. ### Claim 3 (depends on 2) The gas turbine engine of claim 2, wherein the second annular portion is configured to allow access to a plurality of external core features when the second annular portion is arranged in a partially open position. ### Claim 4 (depends on 2) The gas turbine engine of claim 2, wherein the second annular portion is configured to allow access to the engine core when the second annular portion is arranged in a fully open position. ### Claim 5 (depends on 2) The gas turbine engine of claim 2, wherein the first tandem pivot door subassembly forms a first portion of an outer surface of a nacelle when stowed; and the second tandem pivot door subassembly is spaced from the first tandem pivot door subassembly and forms a second portion of the outer surface of the nacelle when stowed, wherein the first and second pivot door subassemblies each form a portion of a surface of a bypass duct when stowed; and when deployed, the first tandem pivot door subassembly and the second tandem pivot door subassembly redirect a fan bypass stream during engine operation while both a core stream and a nacelle ventilation stream flow in substantially a similar manner as when the first and second tandem pivot door subassemblies are stowed. ### Claim 6 (depends on 5) The gas turbine engine of claim 5, wherein the actuator is configured to pivot both the first and second tandem pivot door subassemblies from a stowed position to a deployed position, wherein the actuator is located between the surface of the bypass duct and the outer surface of the nacelle. ### Claim 7 (depends on 2) The gas turbine engine of claim 2, wherein the first inner panel and the first outer panel of the first tandem pivot door subassembly are configured to rotate simultaneously about different pivot axes, and wherein the second inner panel and the second outer panel of the second tandem pivot door subassembly are configured to rotate simultaneously about different pivot axes. ### Claim 8 (depends on 7) The gas turbine engine of claim 7, wherein the actuator is configured to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly from a stowed position to a deployed position, and wherein the respective pivot axes that are each positionally fixed relative to a mounting location. ### Claim 9 (depends on 8) The gas turbine engine of claim 8, wherein a first pivot point of the first inner panel of the first tandem pivot door subassembly is located on the first linkage, and wherein a second pivot point of the first outer panel of the first tandem pivot door subassembly is located at or near a perimeter of the first outer panel of the first tandem pivot door subassembly. ### Claim 10 (depends on 2) The gas turbine engine of claim 2, wherein the first inner panel and the first outer panel are connected so as to rotate simultaneously about different first pivot axes that are positionally fixed with respect to the second annular portion; the second tandem pivot door subassembly is spaced from the first tandem pivot door subassembly; and wherein the second inner panel and the second outer panel are connected so as to rotate simultaneously about different second pivot axes that are positionally fixed with respect to the second annular portion. ### Claim 11 (depends on 10) The gas turbine engine of claim 10, wherein the actuator is configured to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly from a stowed position to a deployed position, and wherein the actuator is located between a surface of a bypass duct and an outer surface of a nacelle. ### Claim 12 (depends on 10) The gas turbine engine of claim 10, wherein in a deployed position during engine operation the first tandem pivot door subassembly and the second tandem pivot door subassembly redirect a fan bypass stream while both a core stream and a nacelle ventilation stream flow in a similar manner as when the first and second tandem pivot door subassemblies are stowed. ### Claim 13 (depends on 2) The gas turbine engine of claim 2, wherein the first inner panel has a first aft edge and a first cutout on the first aft edge corresponding to an inner fixed structure; the first outer panel has a second aft edge; the second inner panel has a third aft edge and a second cutout on the third aft edge corresponding to the inner fixed structure; the second outer panel has a fourth aft edge; and when the first tandem pivot door subassembly and the second tandem pivot door subassembly are in a deployed position the first aft edge of the first inner panel faces toward the third aft edge aft edge of the second inner panel and the second aft edge of the first outer panel faces toward the fourth aft edge of the second outer panel.