Rotating detonation-enabled augmentor systems
Systems and methods are provided herein useful to thrust augmentation in a gas turbine engine. In some embodiments, the systems include augmentors that incorporate a rotating detonation architecture. An exhaust system of a gas turbine engine includes an augmentor and a peripheral wall surrounding an exhaust system core. The augmentor comprises a detonation chamber disposed within the exhaust system core. The detonation chamber includes a channel formed in the peripheral wall. A core inlet path delivers a core air-fuel mixture and a pilot inlet path delivers a pilot air-fuel mixture to the detonation chamber. The core air-fuel mixture combusts in the detonation chamber along the midline the detonation chamber. The pilot air-fuel mixture detonates in the detonation chamber adjacent the peripheral wall to create a rotating detonation wave that supports the combustion reaction occurring along the midline of the detonation chamber.
1. An engine comprising:
a core section; and
an exhaust system positioned downstream of the core section, the exhaust system having an exhaust system core, a peripheral wall surrounding the exhaust system core and an augmentor, the augmentor comprising:
a detonation chamber disposed within at least a portion of the exhaust system core and defined by a portion of the peripheral wall of the exhaust system;
a channel formed in the portion of the peripheral wall defining the detonation chamber, the peripheral wall including a backward-facing step having an opening extending therethrough, a body coupled to the backward-facing step along a border of the opening and disposed upstream of the opening, the body defining a pilot inlet path that delivers a pilot air-fuel mixture through the opening to the detonation chamber, the pilot inlet path in fluid communication with the detonation chamber and a fan of the engine, the pilot inlet path including a fuel delivery orifice upstream of the opening;
a core inlet path in fluid communication with the detonation chamber and a turbine of the engine, wherein the core inlet path delivers a core air-fuel mixture to the detonation chamber; and
wherein the core air-fuel mixture reacts in the detonation chamber along a midline of the detonation chamber, and wherein a portion of the pilot air-fuel mixture reacts in the channel to create a rotating detonation wave.
2. The engine of claim 1 , wherein the rotating detonation wave propagates from the peripheral wall to consume at least a portion of the core air-fuel mixture.
3. The engine of claim 1 , wherein the detonation chamber is unobstructed from the midline of the detonation chamber to the peripheral wall.
4. The engine of claim 1 , wherein the channel includes a forward-facing step.
5. The engine of claim 4 , wherein one or more of the backward-facing step and the forward-facing step is sloped.
6. The engine of claim 1 , wherein the detonation chamber includes a pilot detonation zone adjacent the peripheral wall and a core reaction zone that extends along the midline of the detonation chamber, and wherein the pilot air-fuel mixture reacts in the pilot detonation zone and the core air-fuel mixture reacts in the core reaction zone.
7. The engine of claim 1 , further comprising:
an exhaust nozzle positioned downstream of the detonation chamber,
wherein the exhaust nozzle is at least one of a converging/diverging nozzle or a variable area nozzle.
8. The engine of claim 1 , further comprising:
a core fuel delivery system in fluid communication with the core inlet path, wherein the core fuel delivery system delivers a first fuel to the core inlet path to create the core air-fuel mixture; and
a pilot fuel delivery system in fluid communication with the pilot inlet path, wherein the pilot fuel delivery system delivers a second fuel to the pilot inlet path to create the pilot air-fuel mixture.
9. The engine of claim 8 , wherein the core fuel delivery system is upstream of the detonation chamber.
10. The engine of claim 1 , wherein the detonation chamber lacks a centerbody.
11. The engine of claim 1 , wherein the detonation chamber has a non-circular cross-sectional area.
12. The engine of claim 1 , wherein the channel further includes an igniter operable to ignite the pilot air-fuel mixture.
13. The engine of claim 1 , wherein the detonation chamber further includes an igniter operable to ignite the core air-fuel mixture.
14. The engine of claim 1 , wherein the opening is one of a plurality of openings, the plurality of openings comprising a plurality of circular holes.
15. The engine of claim 1 , wherein the opening is one of a plurality of openings, the plurality of openings comprising a plurality of non-circular holes.
16. A method of operating the engine of claim 1 , the method comprising:
igniting the pilot air-fuel mixture in the detonation chamber to create the rotating detonation wave; and
stabilizing the rotating detonation wave via the channel.
17. The method of claim 16 , further comprising:
supplying a first fuel to core air of the engine to create the core air-fuel mixture; and
supplying a second fuel to fan bypass air of the engine to create the pilot air-fuel mixture.
18. The method of claim 17 , wherein the first fuel is supplied to the core air upstream of the channel.