Engine
First Claim
1. A gas turbine engine comprising a thrust core surrounded by an engine casing, the engine casing including an inlet for an inlet flow to the thrust core, the inlet having a rotor that in use imparts a centrifugal component to the inlet flow, the engine is characterised in that a bypass chute extends between the inlet and the casing, wherein the centrifugal component urges particulate matter in the inlet flow through the bypass chute rather than the thrust core.
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Accused Products
Abstract
In prop fan and contra fan gas turbine engines particularly utilised with regard to pusher configurations towards the aft of an aircraft, there is a significant problem with regard to debris and bird strikes resulting in particulate matter which may damage the engine thrust core. By providing an inlet rotor which fragments and creates a centrifugal aspect to the inlet flow, particulate matter can be directed to a bypass chute normally in the form of an annular section extending into a number of chute exits. In such circumstances, the particulate matter is removed continuously from the inlet flow and the chutes are normally angled to project any particulate matter towards propellers of the engine at robust positions.
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Citations
21 Claims
- 1. A gas turbine engine comprising a thrust core surrounded by an engine casing, the engine casing including an inlet for an inlet flow to the thrust core, the inlet having a rotor that in use imparts a centrifugal component to the inlet flow, the engine is characterised in that a bypass chute extends between the inlet and the casing, wherein the centrifugal component urges particulate matter in the inlet flow through the bypass chute rather than the thrust core.
Specification