ROTATING DETONATION ENGINE WAVE INDUCED MIXER
A rotating detonation engine includes an annulus that defines a volume having a detonation region which is configured for a mixture of an oxidizer and a fuel to detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes an oxidizer outlet configured to output the oxidizer into the volume. The rotating detonation engine further includes a fuel outlet configured to output the fuel into the volume such that the oxidizer and the fuel are initially insufficiently mixed to facilitate combustion. The rotating detonation engine further includes an obstacle positioned upstream from the detonation region and configured to mix the fuel and the oxidizer that are directed upstream in response to a passing detonation.
1 . A rotating detonation engine, comprising:
an annulus that defines a volume having a detonation region which is configured for a mixture of an oxidizer and a fuel to detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows;
an oxidizer outlet configured to output the oxidizer into the volume;
a fuel outlet configured to output the fuel into the volume such that the oxidizer and the fuel are initially insufficiently mixed to facilitate combustion; and
an obstacle positioned upstream from the detonation region and configured to mix the fuel and the oxidizer that are directed upstream in response to a passing detonation.
2 . The rotating detonation engine of claim 1 , wherein the obstacle has a face that faces towards the downstream outlet and extends towards a second wall of the annulus from a first wall of the annulus.
3 . The rotating detonation engine of claim 2 , wherein the face forms an angle with the first wall of the annulus that is between 50 degrees and 120 degrees.
4 . The rotating detonation engine of claim 2 , wherein the face is at least one of straight or concave.
5 . The rotating detonation engine of claim 1 , wherein the oxidizer and the fuel are sufficiently mixed after the passing detonation to facilitate combustion.
6 . The rotating detonation engine of claim 5 , wherein a fuel-air equivalence ratio of the oxidizer and the fuel after the passing detonation is selected based on an oxidizer type of the oxidizer, a fuel type of the fuel, a pressure experienced at a location of mixing, and a temperature experienced at the location of mixing.
7 . The rotating detonation engine of claim 1 , wherein the fuel is injected into the volume in a direction that forms an angle with a first wall of the annulus that is between negative 90 degrees and 90 degrees.
8 . The rotating detonation engine of claim 1 , wherein the fuel outlet includes a first fuel outlet coupled to a first wall of the annulus and a second fuel outlet coupled to a second wall of the annulus.
9 . The rotating detonation engine of claim 1 , wherein the obstacle includes a first face that faces towards the downstream outlet and extends towards a second wall of the annulus from a first wall of the annulus, and a second face that faces towards the downstream outlet and extends towards the first wall of the annulus from the second wall of the annulus.
10 . The rotating detonation engine of claim 1 , wherein the oxidizer is injected into the volume in a direction that forms an angle with a first wall of the annulus that is between negative 90 degrees and 90 degrees.
11 . The rotating detonation engine of claim 1 , wherein the obstacle has an obstacle distance from a first wall of the annulus towards a second wall of the annulus that is equal to between 10 percent and 90 percent of an annulus distance from the first wall to the second wall.
12 . A rotating detonation engine, comprising:
an annulus that defines a volume having a detonation region which is configured for a mixture of an oxidizer and a fuel to detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows;
an oxidizer outlet configured to output the oxidizer into the volume at an oxidizer velocity;
a fuel outlet configured to output the fuel into the volume at a fuel velocity that is within twenty five percent of the oxidizer velocity to create a relatively low shear relationship between the oxidizer and the fuel; and
a face located upstream from the detonation region, at least partially facing towards the downstream outlet, and configured to mix the fuel and the oxidizer that are directed upstream in response to a passing detonation.
13 . The rotating detonation engine of claim 12 , wherein the face forms an angle with a first wall of the annulus that is between 50 degrees and 120 degrees.
14 . The rotating detonation engine of claim 12 , wherein the face is at least one of straight or concave.
15 . The rotating detonation engine of claim 12 , wherein a portion of the fuel fails to combust prior to being directed upstream in response to the passing detonation.
16 . The rotating detonation engine of claim 12 , wherein the face includes a first face that extends towards a second wall of the annulus from a first wall of the annulus, and a second face that extends towards the first wall of the annulus from the second wall of the annulus.
17 . A gas turbine engine, comprising:
a turbine section configured to convert detonation exhaust into torque;
a compressor section configured to receive the torque from the turbine section and to utilize the torque to compress fluid; and
a rotating detonation engine configured to generate the detonation exhaust and having:
an annulus that defines a volume having a detonation region which is configured for a mixture of an oxidizer and a fuel to detonate in a rotating fashion, the volume defining a downstream outlet through which the detonation exhaust flows,
an oxidizer outlet configured to output the oxidizer into the volume,
a fuel outlet configured to output the fuel into the volume such that the oxidizer and the fuel are initially insufficiently mixed to facilitate combustion, and
an obstacle positioned upstream from the detonation region and configured to mix the fuel and the oxidizer that are directed upstream in response to a passing detonation.
18 . The gas turbine engine of claim 17 , wherein the obstacle has a face that faces towards the downstream outlet and extends towards a second wall of the annulus from a first wall of the annulus.
19 . The gas turbine engine of claim 18 , wherein the face is at least one of straight or concave and forms an angle with the first wall of the annulus that is between 50 degrees and 120 degrees.
20 . The gas turbine engine of claim 17 , wherein a portion of the fuel fails to combust prior to being directed upstream in response to the passing detonation.