7 results about "Shock cooling" patented technology

The utility model relates to the rolling technical field, and one embodiment of the utility model provides an elliptical material's control cooling and rolling device, it includes roller group, the outer side of roller group is provided with rolling mechanism, the rolling mechanism includes the side plate of placement in the outer side of roller group, and the inner side between side plate is rotatably installed with roll no. The utility model discloses through making water flow cover more fit elliptical material middle area, avoid edge portion and cool too much while middle part cooling deficiency, compared with traditional elliptical material's control cooling and rolling device, the elliptical material's control cooling and rolling device of this kind through flat ellipse spout setting flat ellipse spout, increase middle part water flow density, improve middle part water flow speed, strengthen the impact cooling effect, solve the uneven cooling problem of elliptical material because of cross section shape, avoid edge portion and cool too much fragile or middle part residual defect, through above technical scheme, solved the technical problem of the poor cooling effect of elliptical material in relevant technology.

An arrangement (1) for the rear impact cooling of an impact plate (2) thermally stressed on its front side (3) by a hot medium (4) comprises the impact plate (2), a perforated plate (6) arranged at a distance from the rear side (5) of the impact plate (2), cooling fluid passage holes in the perforated plate (6) directed towards the rear side (5) of the impact plate (2), a cooling fluid outflow channel (9) formed between the rear side (5) of the impact plate (2) and the perforated plate (6), open in a transverse flow direction (10) at a cooling fluid outlet opening, and a cooling fluid supply channel (13) to which the cooling fluid passage holes are fluidically connected. The cooling fluid supply channel (13), the cooling fluid passage holes, and the cooling fluid outflow channel (9) form a cooling fluid passage through the arrangement (1) that is closed up to the cooling fluid outlet opening.To increase heat transfer from the baffle plate (2) to a cooling fluid (15) flowing through the cooling fluid passage, fluidic oscillators (19) are arranged in the cooling fluid passage.

An integrated combustor nozzle (100) includes a combustion liner (110) extending radially between an inner liner section (106) and an outer liner section (108), the combustion liner (110) including a forward end portion (112), an aft end portion, a first sidewall (116), and a second sidewall (118). The aft end portion (114) of the combustion liner (110) defines a turbine nozzle (120). The combustion liner (110) defines a cavity (126) forward of the turbine nozzle (120). The cavity (126) extends between the first sidewall (116) and the second sidewall (118). An impingement cooling apparatus is positioned within the cavity (126). The impingement cooling apparatus includes a flange (310, 311). The impingement cooling apparatus further includes a plurality of impingement members (302) configured to direct a coolant to impinge on the first sidewall (116) and the second sidewall (118). Each impingement member (302) extends from a respective inlet (313) defined within the flange (310, 311) to a respective closed end (312). A plurality of impingement holes (304) are defined on each impingement member (302).

The invention belongs to the technical field of aero-engine combustion chamber design, and particularly relates to an aero-engine combustion chamber and a flame tube head thereof, and the side wall of the flame tube head is divided into a front side impact wall and a rear side divergence wall; a plurality of turbulent flow columns are arranged between the front side impact wall and the rear side diffusion wall; a plurality of impingement cooling holes are formed in the front side impingement wall, a plurality of diverging cooling holes are formed in the rear side diverging wall, the impingement cooling holes and the diverging holes are distributed in a staggered mode, and turbulent flow columns are arranged between the adjacent impingement cooling holes and diverging holes; the impact cooling holes are gradually shrunk, and the divergent cooling holes are gradually expanded.

This invention discloses a hollow turbine stator structure and its cooling method for a gas turbine, comprising a blade, a core, and a base plate. The blade includes an upper edge plate, a lower edge plate, and a blade body disposed between the upper and lower edge plates. The upper and lower edge plates of the blade are machined with cooling film holes, and the blade body has a composite cooling structure. The core extends longitudinally through the blade, and its upper and lower ends are respectively installed and positioned with the upper and lower edge plates. The middle position is connected to the interior of the blade body. The core is machined with cooling air holes, which can form impact cooling on the inner surface of the blade cavity. The base plate is disposed on the lower surface of the lower edge plate, and a cooling gap is formed between the bottom outlet position of the core and the lower surface of the lower edge plate. The cooling scheme formed by the hollow turbine stator structure of this invention has three cooling paths, which can achieve all-round cooling of the blade.

A combustor (130) for a gas turbine system (100) comprises a laminated (AM) monolithic member (164) having a combustion liner (166) having a transition portion (170) and a rear frame (190) at the rear end (232) of the transition portion (170). The impact cooling structure of the transition portion (170) includes an impact opening (254) leading to an internal impact cavity (256). A coolant passage (260) extends from the internal impact cavity (256) to the rear end (232) of the transition portion (170). The outlet of the coolant passage (260) extends radially inward from the rear end (232) of the transition portion (170) and is located near a rear rail (266) that is axially spaced from the rear frame (190). When operating, the coolant enters the internal collision cavity (256) through the collision opening (254) and then travels through the coolant passage (260) to cool the rear rail (266). The AM combustor body (160) comprises a plurality of parallel metallurgically bonded metal layers (280). The collision cooling structure promotes increased cooling for the rear frame (190) and the combustion liner (166) without loss of structural strength.