Vectoring transition duct for turbine engine
First Claim
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1. A turbine engine assembly comprising:
- a fan including a plurality of fan blades, wherein at least one of the plurality of fan blades defines a centrifugal compressor chamber therein for compressing core airflow therein and guiding the compressed core airflow toward the combustor;
a combustor burning fuel to generate a high-energy gas stream;
a turbine downstream from the combustor, the turbine rotatably drivable by the high-energy gas stream;
a transition duct downstream from the turbine and the fan, the transition duct having a first side and a second side opposite the first side; and
a plurality of variable vanes spaced across the transition duct between the sides for vectoring airflow from the fan and the combustor, wherein each of the plurality of variable vanes is pivoted at an angle, and the angles progressively increase across the transition duct between the first side and the second side.
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Abstract
A transition duct (112) is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine (10) from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of the transition duct. The transition duct incorporates a perimeter slot (124) providing cooling to the duct outer wall and attached components. The variable vanes (120) are installed to vector the exhaust gases. This allows the aircraft to decelerate, hover or accelerate in the forward direction by commanding the position of the variable vanes. One potential application of the tip turbine engine is for vertical installations in aircraft.
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Citations
15 Claims
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1. A turbine engine assembly comprising:
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a fan including a plurality of fan blades, wherein at least one of the plurality of fan blades defines a centrifugal compressor chamber therein for compressing core airflow therein and guiding the compressed core airflow toward the combustor; a combustor burning fuel to generate a high-energy gas stream; a turbine downstream from the combustor, the turbine rotatably drivable by the high-energy gas stream; a transition duct downstream from the turbine and the fan, the transition duct having a first side and a second side opposite the first side; and a plurality of variable vanes spaced across the transition duct between the sides for vectoring airflow from the fan and the combustor, wherein each of the plurality of variable vanes is pivoted at an angle, and the angles progressively increase across the transition duct between the first side and the second side. - View Dependent Claims (2, 3, 4, 5, 6, 7, 13)
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8. A turbine engine and controller comprising:
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a bypass fan including a plurality of fan blades, at least one of the fan blades defining a centrifugal compressor chamber therein for centrifugally compressing core airflow; a combustor burning fuel mixed with the compressed core airflow from the centrifugal compressor chamber to generate a high-energy gas stream; a turbine downstream from the combustor, the turbine rotatably driven by the high-energy gas stream, the turbine rotatably driving the bypass fan; a transition duct downstream from at least one of the turbine and the fan, the transition duct transitioning air flow through the transition duct from a generally round cross-section to a generally rectangular cross-section; a transition duct downstream from the turbine and the fan, the transition duct having a first side and a second side opposite the first side; and a plurality of variable vanes spaced across the transition duct between the sides for vectoring airflow from the fan and the combustor, wherein each of the plurality of variable vanes is pivoted at an angle, and the angles progressively increase across the transition duct between the first side and the second side. - View Dependent Claims (9, 10, 11, 12)
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14. A turbine engine comprising:
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a transition duct mounted proximate an outlet of the turbine engine having an outer wall defining an interior between an inlet and an outlet; a plurality of variable vanes pivotably mounted to the outer wall proximate the outlet for vectoring airflow through the interior; a vent through the outer wall between the inlet and the plurality of variable vanes, the vent extending entirely about an outer perimeter of the outer wall; and wherein the turbine engine includes a fan having a plurality of fan blades including at least one hollow fan blade having a core airflow compressor chamber defined therein. - View Dependent Claims (15)
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Specification