CONTINUOUS DETONATION WAVE TURBINE ENGINE
A gas turbine engine includes a transient plasma igniter in communication with a continuous detonation wave combustor. A method of operating a gas turbine engine includes maintaining ignition of a continuous detonation wave combustor with a transient plasma igniter.
1 . A gas turbine engine, comprising:
a tip turbine engine compressor;
a continuous detonation wave combustor in fluid communication with and downstream of said compressor;
a turbine in fluid communication with and downstream of said continuous detonation wave combustor; and
a transient plasma ignitor in communication with said continuous detonation wave combustor.
2 . The gas turbine engine as recited in claim 1 , further comprising a high bypass fan section upstream of said tip turbine engine compressor.
3 . The gas turbine engine as recited in claim 1 , further comprising a centrifugal compressor gas turbine engine architecture.
4 . A gas turbine engine, comprising:
a continuous detonation wave combustor; and
a transient plasma ignitor in communication with said continuous detonation wave combustor.
5 . The gas turbine engine as recited in claim 4 , further comprising a fan-turbine rotor assembly with a multiple of hollow fan blades to provide internal, centrifugal compression of a compressed airflow to said continuous detonation wave combustor.
6 . The gas turbine engine as recited in claim 5 , further comprising an axial compressor axially forward of said fan-turbine rotor assembly.
7 . The gas turbine engine as recited in claim 5 , wherein said continuous detonation wave combustor is radially outboard of said multiple of hollow fan blades.
8 . The gas turbine engine as recited in claim 5 , wherein each of said multiple of hollow fan blades include a fan blade core airflow passage generally perpendicular to an axis of rotation of said fan-turbine rotor assembly.
9 . The gas turbine engine as recited in claim 4 , further comprising a centrifugal compressor gas turbine engine architecture.
10 . The gas turbine engine as recited in claim 9 , further comprising a high bypass fan section.
11 . A method of operating a gas turbine engine, the method comprising:
maintaining ignition of a continuous detonation wave combustor with a transient plasma igniter.
12 . The method as recited in claim 11 , further comprising:
internally compressing an airflow within a fan-turbine rotor assembly; and
communicating the airflow from the fan-turbine rotor assembly to the continuous detonation wave combustor.
13 . The method as recited in claim 12 , further comprising:
axially compressing the airflow upstream of the fan-turbine rotor assembly.
14 . The method as recited in claim 11 , further comprising:
generating a compression ratio of about forty to one (40:1) within the continuous detonation wave combustor.
15 . The method as recited in claim 11 , further comprising:
centrifugally compressing an airflow within a high bypass gas turbine engine architecture.
16 . The method as recited in claim 11 , further comprising:
centrifugally compressing an airflow within a low bypass gas turbine engine architecture.