【EP3561237A1】VARIABLEVANESYSTEMWITHCOOLINGFLOWMODU

EP 3 561 237 A1
Printed by Jouve, 75001 PARIS (FR)
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EP 3 561 237 A1
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Description
embodiments of the present disclosure includes a trailing
edge cavity.
BACKGROUND
a gas turbine engine.
embodiments of the present disclosure includes a cooling
[0002] Gas turbine engines, such as those that power
cavity that provides airfoil cooling utilizing convective
(22) Date of filing: 23.04.2019
(51) Int Cl.: F01D 9/06 (2006.01)
F01D 17/16 (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: 27.04.2018 US 201815965130
(71) Applicant: United Technologies Corporation Farmington, CT 06032 (US)
(72) Inventor: ANDERSON, Corey D. East Hartford CT 06118 (US)
modern commercial and military aircraft, generally in- 10 heat transfer.
clude a compressor section to pressurize an airflow, a
[0013] A further embodiment of any of the foregoing
(74) Representative: Dehns St. Bride’s House 10 Salisbury Square London EC4Y 8JD (GB)
(54) VARIABLE VANE SYSTEM WITH COOLING FLOW MODULATION
(57) A variable vane system for a gas turbine engine includes an airfoil trunnion (84) that extends through a vane platform (72) such that the airfoil (78) is rotatable with respect to the vane platform (72) about an axis (W), the airfoil trunnion (84) having an inlet configuration (120) into the airfoil (78) and a fixed airflow inlet mask (85) to
purge feed cavity.
engine and, more particularly, to a system and method
ing.
ຫໍສະໝຸດ Baidu
of modulating an airflow into a variable vane system for
[0012] A further embodiment of any of the foregoing
abut the airfoil trunnion (84), the fixed airflow inlet mask (85) having a mask inlet configuration (110), rotation of the airfoil (78) rotates the trunnion inlet configuration (120) with respect to the fixed airflow inlet mask (85) to change an effective flow into the airfoil (78).
combustor section for burning a hydrocarbon fuel in the
embodiments of the present disclosure includes a rotor
presence of the pressurized air, and a turbine section to
[0011] A further embodiment of any of the foregoing
embodiments of the present disclosure includes an airfoil
[0001] The present disclosure relates to a gas turbine 5 cavity that ejects cooling flow to the gaspath via film cool-
(19)
*EP003561237A1*
(11)
EP 3 561 237 A1
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EUROPEAN PATENT APPLICATION
(43) Date of publication: 30.10.2019 Bulletin 2019/44
(21) Application number: 19170661.3