Patent SG-11201407138Q-A (SG)
Title: Gas turbine engine oil tank
Inventor: SUCIU GABRIEL L
IPC: F02K3/02
Filed: 2013-04-25
Abstract: (12) INTERNATIONAL APPLICATION PUBLISHED UNDER THE PATENT COOPERATION TREATY (PCT) (19) World Intellectual Property Organization International Bureau (43) International Publication Date 14 November 2013 (14.11.2013) WIPOIPCT (10) International Publication Number WO 2013/169495 A1 (51) International Patent Classification: F02C 7/06 (2006.01) F01M11/00 (2006.01) F02C 7/00 (2006.01) (21) International Application Number: (22) International Filing Date: (25) Filing Language: (26) Publication Language: PCT/US2013/038231 25 April 2013 (25.04.2013) English (30) Priority Data: 13/465,637 7 May 2012 (07.05.2012) English US (71) Applicant: UNITED TECHNOLOGIES CORPORA­ TION [US/US]; One Financial Plaza, Hartford, Connectic­ ut 06101 (US). (72) Inventors: SUCIU, Gabriel L.; 27 Tanglewood Drive, Glastonbury, Connecticut 06033 (US). SNAPE, Nathan; 520 Mile Hill Rd„ Tolland, Connecticut 06084 (US). DYE, Christopher M.; 3131 Clairemont Drive, Apt. 3, San Diego, California 92117 (US). (74) Agent: GOTTSCHALK, William S.; Carlson,Gaskey & Olds/Pratt & Whitney, c/o CPA Global, PO Box 52050, Minneapolis, Minnesota 55402 (US). (81) Designated States (unless otherwise indicated, for every kind of national protection available)'. AE, AG, AL, AM, AO, AT, AU, AZ, BA, BB, BG, BH, BN, BR, BW, BY, BZ, CA, CH, CL, CN, CO, CR, CU, CZ, DE, DK, DM, DO, DZ, EC, EE, EG, ES, FI, GB, GD, GE, GH, GM, GT, HN, HR, HU, ID, IL, IN, IS, JP, KE, KG, KM, KN, KP, KR, KZ, LA, LC, LK, LR, LS, LT, LU, LY, MA, MD, ME, MG, MK, MN, MW, MX, MY, MZ, NA, NG, NI, NO, NZ, OM, PA, PE, PG, PH, PL, PT, QA, RO, RS, RU, RW, SC, SD, SE, SG, SK, SL, SM, ST, SV, SY, TH, TJ, TM, TN, TR, TT, TZ, UA, UG, US, UZ, VC, VN, ZA, ZM, ZW. (84) Designated States (unless otherwise indicated, for every kind of regional protection available)'. ARIPO (BW, GH, GM, KE, LR, LS, MW, MZ, NA, RW, SD, SL, SZ, TZ, UG, ZM, ZW), Eurasian (AM, AZ, BY, KG, KZ, RU, TJ, TM), European (AL, AT, BE, BG, CH, CY, CZ, DE, DK, EE, ES, FI, FR, GB, GR, HR, HU, IE, IS, IT, LT, LU, LV, MC, MK, MT, NL, NO, PL, PT, RO, RS, SE, SI, SK, SM, TR), OAPI (BF, BJ, CF, CG, CI, CM, GA, GN, GQ, GW, ML, MR, NE, SN, TD, TG). Published: — with international search report (Art. 21(3)) — before the expiration of the time limit for amending the claims and to be republished in the event of receipt of amendments (Rule 48.2(h)) [Continued on next page] (54) Title: GAS TURBINE ENGINE OIL TANK (57) Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. Fan and core nacelles define an annular bypass flow path. The core nacelle provides a core compart­ ment and includes an opening into the core compartment. The oil tank is arranged in the core compartment and includes a portion aligned with the opening that is exposed to the bypass flow path. The engine static structure is supported relative to a fan case by a radial structure. The oil tank is mounted to the engine static structure. An oil fill tube is mounted to the fan case and is fluidly connected to the oil tank. FIG.1 WO 2013/169495 A11 lllll llllllll II llllll III lllll lllll III III III lllll lllll lllll llll llll lllll lllll lllllll llll llll — with information concerning incorporation by reference of missing parts and/or elements (Rule 20.6)