Gas turbine engine with integral actuation system
An engine system is provided that includes a gas turbine engine and an actuation system. The gas turbine engine includes a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The actuation system includes a fluid reservoir, a flow regulator and a flow circuit. The flow regulator is configured as or otherwise includes a barrier between the fluid reservoir and the flow circuit. The flow regulator is configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact. The flow regulator is configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks. The flow circuit is configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks.
1. An engine system, comprising:
a gas turbine engine including a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section, the compressor section comprising a compressor rotor, and the turbine section comprising a turbine rotor configured to drive rotation of the compressor rotor;
an actuation system including a fluid reservoir, a flow regulator and a flow circuit, the flow regulator comprising a barrier between the fluid reservoir and the flow circuit, the flow regulator configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact, the flow regulator configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks, and the flow circuit configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks, wherein the barrier is integral with a wall of the fluid reservoir, and the barrier comprises a wall with a stress concentrator; and
an ignitor configured to explode to ignite fuel within the fluid reservoir to provide the gas.
2. The engine system of claim 1 , wherein, when the barrier breaks, the barrier is configured to burst open without liberating debris into the flow circuit.
3. The engine system of claim 1 , wherein the stress concentrator comprises a groove.
4. The engine system of claim 3 , wherein the wall further includes a second stress concentrator that intersects the stress concentrator.
5. The engine system of claim 1 , wherein the flow circuit is configured to direct the gas into the flowpath within the turbine section when the barrier breaks.
6. The engine system of claim 1 , wherein the flow circuit is configured to direct the gas into the flowpath to drive rotation of the turbine rotor when the barrier breaks.
7. The engine system of claim 1 , wherein the flow circuit includes
a base passage;
a first branch passage extending out from the base passage to a first outlet along the flowpath; and
a second branch passage extending out from the base passage to a second outlet along the flowpath.
8. The engine system of claim 7 , wherein a length of the first branch passage is equal to a length of the second branch passage.
9. The engine system of claim 7 , wherein the first outlet and the second outlet are aligned longitudinally along the flowpath.
10. The engine system of claim 1 , wherein
the gas turbine engine further includes a plurality of vanes arranged in an array and extending across the flowpath; and
the flow circuit extends through a first of the plurality of vanes.
11. The engine system of claim 1 , wherein
the gas turbine engine further includes a wall forming a peripheral boundary of the flowpath; and
the flow circuit extends circumferentially about a centerline of the gas turbine engine within the wall.
12. The engine system of claim 1 , wherein
the gas turbine engine comprises a stationary structure and a rotating structure at least partially housed within the stationary structure;
the fluid reservoir and the stationary structure are included in a monolithic body; and
the rotating structure includes the compressor rotor and the turbine rotor.
13. The engine system of claim 12 , wherein the flow circuit comprises a passage formed by and within the monolithic body.
14. An engine system, comprising:
a gas turbine engine;
a fluid reservoir for the gas turbine engine;
a burst plate integral with a sidewall of the fluid reservoir, the burst plate comprising a passage barrier with one or more stress concentrators; and
an ignitor configured to explode to ignite fuel within the fluid reservoir.