Inlet bleed heat control system
The present application provides an inlet bleed heat control system for a compressor of a gas turbine engine. The inlet bleed heat control system provides an inlet bleed heat manifold and an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient air.
1. An inlet bleed heat control system for a compressor of a gas turbine engine, comprising:
an inlet bleed heat manifold; and
an ejector in communication with the inlet bleed heat manifold;
the ejector in communication with a flow of compressor discharge air and a flow of ambient air;
wherein the ejector is in communication with a filter house line with the flow of ambient air; and
wherein the filter house line comprises a filter house line valve thereon.
2. The inlet bleed heat control system of claim 1 , wherein the ejector is in communication with a compressor discharge line with the flow of compressor discharge air.
3. The inlet bleed heat control system of claim 2 , wherein the compressor discharge line comprises a compressor discharge valve thereon.
4. The inlet bleed heat control system of claim 3 , wherein the compressor discharge line comprises an ejector valve thereon.
5. The inlet bleed heat control system of claim 1 , further comprising an ejector bypass line positioned between the compressor and the inlet bleed heat manifold.
6. The inlet bleed heat control system of claim 5 , wherein the bypass line comprises a bypass valve thereon.
7. The inlet bleed heat control system of claim 1 , wherein the inlet bleed heat manifold comprises a plurality of acoustic nozzles.
8. The inlet bleed heat control system of claim 1 , further comprising a controller.
9. The inlet bleed heat control system of claim 8 , wherein the controller comprises anti-icing signals.
10. The inlet bleed heat control system of claim 8 , wherein the controller comprises operating limit line signals.
11. The inlet bleed heat control system of claim 1 , further comprising a filter house upstream of the inlet bleed heat manifold.
12. The inlet bleed heat control system of claim 1 , further comprising a plurality of inlet guide vanes downstream of the inlet bleed heat manifold.
13. A method of operating an inlet bleed heat control system, comprising:
determining if operational parameters require inlet bleed heat;
opening a compressor discharge line to an ejector;
opening a filter house line to the ejector;
mixing compressor discharge air and ambient air in the ejector;
flowing the mixed air to an inlet bleed heat manifold; and
determining if the operational parameters have been achieved by the mixed flow.
14. An inlet bleed heat control system for a compressor of a gas turbine engine, comprising:
an inlet bleed heat manifold;
an ejector in communication with the inlet bleed heat manifold;
the ejector in communication with a flow of compressor discharge air and a flow of ambient air to create a mixed flow; and
a bypass line in communication with the compressor and the inlet bleed heat manifold.
15. The inlet bleed heat control system of claim 14 , wherein ejector is in communication with a filter house line with a filter house line valve thereon.
16. The inlet bleed heat control system of claim 14 , wherein the ejector is in communication with a compressor discharge line with a compressor discharge valve thereon and an ejector valve thereon.
17. The inlet bleed heat control system of claim 14 , wherein the bypass line comprises a bypass valve thereon.
18. The inlet bleed heat control system of claim 14 further comprising a controller with anti-icing signals and operating limit line signals.