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In a turbomachine having an inlet, a compressor, and a turbine, a closed loop sends fluid from a stage of the compressor to a heat exchanger in the turbine and to the inlet. The closed loop heats the fluid, cools the turbine, and delivers heated fluid to the inlet. A mixer can be interposed between

In a turbomachine having an inlet, a compressor, and a turbine, a closed loop sends fluid from a stage of the compressor to a heat exchanger in the turbine and to the inlet. The closed loop heats the fluid, cools the turbine, and delivers heated fluid to the inlet. A mixer can be interposed between the heat exchanger and the inlet to mix fluid from the heat exchanger with compressor discharge fluid, delivering the mixed fluid to the inlet. The mixer can control flow received so that desired temperature and/or flow rate can be provided to the inlet.

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1. A turbomachine inlet bleed heating assembly comprising: a cavity located at a stage of a turbine of the turbomachine between an inner casing and an outer casing of the turbine, the cavity being substantially sealed against fluid communication with the stage of the turbine;a first conduit configur

1. A turbomachine inlet bleed heating assembly comprising: a cavity located at a stage of a turbine of the turbomachine between an inner casing and an outer casing of the turbine, the cavity being substantially sealed against fluid communication with the stage of the turbine;a first conduit configured for fluid communication with a stage of a compressor of the turbomachine and with the cavity; anda second conduit configured for fluid communication with the cavity and with a compressor inlet of the turbomachine. 2. The turbomachine inlet bleed heating assembly of claim 1, wherein the cavity is located at a plurality of stages of the turbine. 3. The turbomachine inlet bleed heating assembly of claim 1, wherein the cavity includes at least one wall extending between the inner and outer casings. 4. The turbomachine inlet bleed heating assembly of claim 3, wherein the at least one wall includes at least one dividing wall extending substantially parallel to a longitudinal axis of the turbine. 5. The turbomachine inlet bleed heating assembly of claim 3, wherein the at least one wall includes at least two opposed, spaced apart end walls extending substantially perpendicular to a longitudinal axis of the turbine. 6. The turbomachine inlet bleed healing assembly of claim 3, further comprising at least one baffle extending substantially parallel to at least one of the inner casing or the outer casing and configured to provide fluid communication from the first conduit to at least one turbine blade cooling passage and from the at least one turbine blade cooling passage to the second conduit. 7. The turbomachine inlet bleed heating assembly of claim 1, further comprising: a mixer interposed between the second conduit and the compressor inlet;a third conduit configured for fluid communication with a discharge of the compressor and in fluid communication with the mixer; anda fourth conduit in fluid communication with the mixer and configured for fluid communication with the compressor inlet of the turbomachine, fluid received by the mixer from the second and third conduits being mixed to form a mixed flow passed to the fourth conduit by the mixer. 8. The turbomachine inlet bleed heating assembly of claim 7, wherein the mixer includes at least one valve configured to vary a flow rate of each of the second and third conduits. 9. The turbomachine inlet bleed heating assembly of claim 8, further comprising a controller in communication with the at least one valve and configured to control the at least one valve responsive to at least one of a desired temperature or a desired flow rate of the mixed flow. 10. The turbomachine inlet bleed heating assembly of claim 9, wherein the inlet bleed heating assembly includes a plurality of walls forming a respective plurality of cavities between the inner and outer casings. 11. A turbomachine comprising: a compressor inlet;a compressor in fluid communication with the compressor inlet and including at least one stage and a compressor discharge;a turbine in fluid communication with the compressor discharge and including at least one stage;a cavity located at a stage of the turbine between an inner casing and an outer casing of the turbine, the cavity being substantially sealed against fluid communication with the stage of the turbine;a first conduit in fluid communication with a stage of the compressor and the cavity at the stage of the turbine; anda second conduit in fluid communication with the cavity at the stage of the turbine and with the compressor inlet. 12. The turbomachine of claim 11, further comprising a mixer interposed between the second conduit and the compressor inlet, and a third conduit in fluid communication with the compressor discharge and the mixer such that fluid received from the second and third conduits is mixed to produce a mixed flow that is delivered to the compressor inlet. 13. The turbomachine of claim 12, wherein the mixer is configured to vary a respective flow from each of the second and third conduits responsive to an operating condition of the turbomachine, and to send the mixed flows through a fourth conduit to the compressor inlet. 14. The turbomachine of claim 11, further comprising a dividing wall extending between the inner and outer casings substantially parallel to a longitudinal axis of the turbine, and opposed end walls extending between the inner and outer casings substantially perpendicular to the longitudinal axis and connected to the dividing wall. 15. The turbomachine of claim 14, further comprising a plurality of dividing walls extending between the inner and outer casings and the end walls to form a respective plurality of cavities, each cavity having a respective first conduit and a respective second conduit. 16. The turbomachine of claim 14, wherein the cavity is in fluid communication with at least one turbine blade.