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AssigneeMitsubishi Heavy Industries, Ltd.
InventorsYasuhiro Ojiro, Kouichi Akagi, Ryotaro Magoshi, Hitoshi Morimoto, Shinya Hashimoto, Tadao Yashiki
Estimating the term…
Gas turbine blade ring is cooled by steam of which temperature, pressure and flow rate are controlled so that clearance between moving blade tip and blade ring is maintained appropriately. Steam from steam turbine bottoming cycle (10) flows into blade ring cooling passage (8) of gas turbine (1) via piping (12) for cooling blade ring. The steam having cooled the blade ring is supplied into transition piece cooling passage (9) of combustor (3) for cooling transition piece and is then recovered into the steam turbine bottoming cycle (10) via piping (14). While the steam cools the blade ring, temperature, pressure and flow rate of the steam are controlled so that thermal elongation of the blade ring is adjusted and the clearance at the moving blade tip is controlled so as to approach target value. Thus, the clearance is maintained as small as possible in operation and gas turbine performance is enhanced.
A gas turbine comprising a moving blade and a blade ring confronting a tip of said moving blade, wherein a cooling passage is provided in said blade ring and an auxiliary boiler and a steam supply source connecting to a steam turbine bottoming cycle are connected to said cooling passage, so that steam of said auxiliary boiler or said steam supply source is flown into said cooling passage for cooling said blade ring and the steam having cooled said blade ring is recovered, and thereby a clearance between said tip of the moving blade and said blade ring is reduced.
A gas turbine comprising a moving blade and a blade ring confronting a tip of said moving blade as well as comprising a combustor and a transition piece contained in said combustor, wherein a cooling passage is provided in said blade ring, so that steam of a steam supply source is flown into said cooling passage for cooling said blade ring and the steam having cooled said blade ring is flown into said transition piece via a combustor transition piece connection portion for cooling a wall interior of said transition piece and the steam having cooled said wall interior of the transition piece is recovered into said steam supply source, and thereby a clearance between said tip of the moving blade and said blade ring is reduced.
A gas turbine comprising a moving blade and a blade ring confronting a tip of said moving blade as well as comprising a combustor and a transition piece contained in said combustor, wherein a cooling passage is provided in said blade ring, so that steam of a steam supply source is flown in parallel into said cooling passage for cooling said blade ring and into said transition piece via a combustor transition piece connection portion for cooling a wall interior of said transition piece and the steam having cooled said blade ring and said wall interior of the transition piece is recovered into said steam supply source, and thereby a clearance between said tip of the moving blade and said blade ring is reduced.
A gas turbine comprising a first stage stationary blade and a first stage moving blade and a blade ring confronting a tip of said first stage moving blade as well as comprising a combustor and a transition piece contained in said combustor, wherein a blade ring cooling passage is provided in said blade ring and a stationary blade cooling passage is provided in said first stage stationary blade so as to connect to said blade ring cooling passage, so that steam of a steam supply source is flown into said blade ring cooling passage for cooling said blade ring and the steam having cooled said blade ring is flown into said stationary blade cooling passage for cooling said first stage stationary blade and the steam having cooled said first stage stationary blade is flown into said transition piece via a combustor transition piece connection portion for cooling a wall interior of said transition piece and the steam having cooled said wall interior of the transition piece is recovered into said steam supply source, and thereby a clearance between said tip of the first stage moving blade and said blade ring is reduced.
A gas turbine comprising a first stage stationary blade and a first stage moving blade and a blade ring confronting a tip of said first stage moving blade as well as comprising a combustor and a transition piece contained in said combustor, wherein a blade ring cooling passage is provided in said blade ring and a stationary blade cooling passage is provided in said first stage stationary blade so as to connect to said blade ring cooling passage, so that steam of a steam supply source is flown in parallel into said blade ring cooling passage for cooling said blade ring and into said stationary blade cooling passage for cooling said first stage stationary blade and the steam having cooled said first stage stationary blade is flown into said transition piece via a combustor transition piece connection portion for cooling a wall interior of said transition piece and the steam having cooled said blade ring and said wall interior of the transition piece is recovered into said steam supply source, and thereby a clearance between said tip of the first stage moving blade and said blade ring is reduced.
Dependencies are inferred from the claim text.