(19)
(11)EP 3 628 820 A3

(12)EUROPEAN PATENT APPLICATION

(88)Date of publication A3:
03.06.2020 Bulletin 2020/23

(43)Date of publication A2:
01.04.2020 Bulletin 2020/14

(21)Application number: 19199806.1

(22)Date of filing:  26.09.2019
(51)International Patent Classification (IPC): 
F01D 9/02(2006.01)
F01D 25/34(2006.01)
F01D 21/00(2006.01)
(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated Extension States:
BA ME
Designated Validation States:
KH MA MD TN

(30)Priority: 26.09.2018 US 201816142317

(71)Applicant: United Technologies Corporation
Farmington, CT 06032 (US)

(72)Inventor:
  • EPSTEIN, Alan H.
    Lexington, MA Massachusetts 02421 (US)

(74)Representative: Dehns 
St. Bride's House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)

  


(54)GAS TURBINE ENGINE SYSTEM COOLDOWN


(57) An engine system for an aircraft (100) includes a first gas turbine engine (20A), a first core turning system (202A), a second gas turbine engine (20B), and a second core turning system (202B). The engine system also includes a controller (214) operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.







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