Gas turbine blade with improved cooling

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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416 96R, F01D 518

Patent

active

053870867

ABSTRACT:
A turbine blade is provided which includes an airfoil section having a leading edge flow region and a trailing edge flow region. The leading edge flow region includes an inner cavity having a serpentine geometry and first and second air inlets. The first air inlet is at one end of the inner cavity and is coupled to a first conduit which supplies air coolant thereto. The leading edge flow region also includes a leading edge cavity having a plurality of air film holes at the leading edge of the blade. The leading edge cavity is coupled to the inner cavity by impingement holes therebetween. The leading edge flow region further includes a refresher passageway which connects the first conduit at the base of the blade with the second inlet of the inner cavity. The refresher passageway refreshes the airflow in the inner cavity after the airflow has flowed part way through the inner cavity and has become warmed. The trailing edge flow region includes a trailing edge cavity which is isolated from the inner cavity and which is cooled by air from a second conduit at the base of the blade. The disclosed turbine blade structure advantageously avoids gas ingestion and backflow margin problems.

REFERENCES:
patent: 3533711 (1970-10-01), Kercher
patent: 4073599 (1978-02-01), Allen et al.
patent: 4162136 (1979-07-01), Parkes
patent: 4278400 (1981-07-01), Yamarik et al.
patent: 4474532 (1984-10-01), Pazder
patent: 4515526 (1985-05-01), Levengood
patent: 4775296 (1988-10-01), Schwarzmann et al.
patent: 4786233 (1988-11-01), Shizuya et al.
patent: 4992026 (1991-02-01), Ohtomo et al.

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