Scoop of a running-gap control system of an aircraft gas turbine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsPredrag Todorovic, Stephan Herzog, Christian Seydel
Life of this patent
Estimating the term…
Abstract
A scoop for a fairing 1 of a core engine 2 of an aircraft gas turbine allows air to be supplied from a bypass flow in a bypass duct 3 to several cooling-air distributors in a core-engine ventilation compartment 4. The scoop includes a first tubular flow duct 5, whose inlet opening 6 is arranged in the bypass duct 3 and which extends through the fairing 1, as well as a second tubular flow duct 7, which at least partly encompasses the first flow duct 5 and whose inlet opening 8 is rearwardly offset relative to the inlet opening 6 of the first flow duct 5 in the direction of flow.
Claims16
An air scoop of a fairing of a core engine of an aircraft gas turbine through which air can be supplied from a bypass flow in a bypass duct to a plurality of cooling-air distributors in a core-engine ventilation compartment, the scoop comprising:
- a first tubular flow duct having an internal passage and an inlet opening arranged in the bypass duct open to the bypass flow, the first tubular flow duct extending through the fairing;
- a second tubular flow duct having an internal passage and an inlet opening arranged in the bypass duct open to the bypass flow, the internal passage and inlet opening of the second tubular flow duct at least partly encompassing the first tubular flow duct, the inlet opening of the second tubular flow duct offset downstream relative to the inlet opening of the first tubular flow duct with respect to a direction of the bypass flow.
Dependencies are inferred from the claim text.