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US 2008/0155959 A1Published application
Detonation combustor to turbine transition piece for hybrid engine
AssigneeGeneral Electric Company
InventorsAdam Rasheed, Anthony John Dean, James Fredric Wiedenhoefer, Venkat Eswarlu Tangirala, Narendra Digamber Joshi
Life of this patent
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Abstract
A transition piece for use within a gas turbine engine provides a path between the exhaust from one or more pressure-rise combustors and a downstream turbine for the extraction of work from the exhaust flow. The transition piece provides a non-expanding path for the exhaust flow through the transition piece, and directs the flow so as to be effective in driving the turbine when it reaches the end of the transition piece.
Claims25
A transition piece for use within a gas turbine engine comprising:
- an exhaust face in flow communication with an exhaust of a pulse detonation combustor of the gas turbine engine located upstream of the exhaust face;
- a body in flow communication with the exhaust face and connected to the exhaust face and the body having a cross section taken normal to the axis of the gas turbine engine such that the area of the cross section at any given point along the axis of the gas turbine engine is smaller than the area of the cross section of the body at any point along the axis of the gas turbine engine upstream of the given point;
- and
- a turbine inlet face in flow communication with a turbine stage of the gas turbine engine, the turbine stage being located downstream of the turbine inlet face, and the turbine inlet face being in flow communication with the body of the transition piece.
1 more element
A hybrid gas turbine engine comprising:
- a plurality of pulse detonation combustors disposed around an axis of the gas turbine engine;
- a transition piece disposed downstream of the pulse detonation combustors and in flow communication with at least one of the plurality of pulse detonation combustors;
- a turbine disposed downstream of the transition piece and in flow communication with the transtition piece;
- the transition piece comprising
- an exhaust face in flow communication with the at least one pulse detonation combustor;
- a body in flow communication with the exhaust face and connected to the exhaust face and the body having a cross section taken normal to the axis of the gas turbine engine such that the area of the cross section at any given point along the axis of the gas turbine engine is smaller than the area of the cross section of the body at any point along the axis of the gas turbine engine upstream of the given point;
- and
- a turbine inlet face in flow communication with the turbine and the body of the transition piece.
5 more elements
Dependencies are inferred from the claim text.