摘要:
A system for supplying a working fluid to a combustor (16) includes a fuel nozzle and a combustion chamber (40) downstream from the fuel nozzle. A flow sleeve (50) circumferentially surrounds the combustion chamber (40), and fuel injectors (60) provide fluid communication to the combustion chamber (40). A distribution manifold (62) circumferentially surrounds the fuel injectors (60) and defines an annular plenum (64). A fluid passage (66) through the distribution manifold (62) provides fluid communication through the distribution manifold (62). A radial cross-sectional area (70) of the annular plenum (64) varies around the flow sleeve (50). A method for supplying a working fluid to a combustor (16) includes flowing a working fluid through a combustion chamber (40), diverting a portion of the working fluid (24) through a distribution manifold (62) that circumferentially surrounds fuel injectors (60) circumferentially arranged around the combustion chamber (40), and changing at least one of a pressure or flow rate of the diverted portion of the working fluid.
摘要:
The invention relates to a wall element (100) for a gas turbine. The wall element (100) comprises a surface running along a surface plane (103) of the wall element (100). The surface comprises a profile (110) extending from the surface plane (103), wherein the profile (110) has a cross section within a cross section plane (106) which is perpendicular to the surface plane (103). The profile (110) comprises along a direction (107) being orientated parallel to the surface plane (103)a first section (I) which runs from the surface plane (103) to a first elevation plane (101) which is parallel to the surface plane (103) and which is spaced from the surface plane (103), a second section (II) which runs from the first elevation plane (101) to a second elevation plane (102) which is parallel to the surface plane (103) and which is located between the first elevation plane (101) and the surface plane (103), a third section (III) which runs from the second elevation plane (102) to the first elevation plane (101) and a fourth section (IV) which runs from the first elevation plane (101) to the surface plane (103).
摘要:
A base plate is more effectively cooled, and the efficiency of cooling the base plate is further improved. In a heat exchange bulkhead 1 that includes a base plate 20 and a plurality of pin-fins 21 provided upright on the surface 20a of the base plate 20, a cooling medium 18 flows in the length direction of the base plate 20 along the surface 20a of the base plate 20, and each of the pin-fins 21 is entirely or partially inclined backward to the downstream side such that the top face thereof is located at the downstream side of the bottom face thereof.
摘要:
Es wird eine Gasturbinenbrennkammer (25) mit im Wesentlichen rotationssymmetrischem Querschnitt zur Verfügung gestellt. Sie weist eine innere Wand (39) mit einer Außenseite und eine äußere Wand (37) mit einer der Außenseite der inneren Wand zugewandten und von dieser beabstandeten Innenseite auf, so dass zwischen der Außenseite der inneren Wand (39) und der Innenseite der äußeren Wand (37) ein wenigstens einen Kühlfluidkanal bildender Zwischenraum (41) vorhanden ist. Die Außenseite der inneren Wand (39) weist in Richtung auf die Innenseite der äußeren Wand (37) vorstehende Kühlrippen auf, wobei die Kühlrippen (43) helixförmig um die innere Wand herum gewunden sind.
摘要:
A combustor assembly (10) for a turbine engine includes a combustor liner (12), a flow sleeve (14) and a plenum ring (36). The flow sleeve surrounds the combustor liner to form an annulus (26) radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes (24). The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes (38) for directing axial air flow and radial flow chambers (40) for directing radial air flow.
摘要:
Bei einer Gasturbine (1) mit einer Anzahl von jeweils zu Laufschaufelreihen zusammengefassten, an einer Turbinenwelle (8) angeordneten Laufschaufeln (12) und mit einer Anzahl von jeweils zu Leitschaufelreihen zusammengefassten, mit einem Turbinengehäuse (16) verbundenen Leitschaufeln (14) sowie mit einer Anzahl von heißgasführenden Komponenten, in deren einen Heißgas-Strömungsraum (36) begrenzende Außenwand (28) jeweils eine Anzahl von Kühlkanälen (32) zur Beaufschlagung mit einem Kühlmedium integriert ist, soll der selbst im Hinblick auf das beschränkte Platzangebot und einen aus Wirkungsgradgründen angestrebten niedrigen Druckverlust eine ausreichende Kühlwirkung an den thermisch besonders belasteten Bereichen der jeweiligen Komponente sicher erzielt werden können. Dazu ist zumindest einer der in die Außenwand (28) der jeweiligen Komponente integrierten Kühlkanäle (32) an seiner vom Heißgas-Strömungsraum (36) abgewandten Innenwand (38) mit turbulenzerzeugenden Strukturelementen (34) versehen.
摘要:
The invention relates to a machine component with a base (40) made of a base material, a part of the surface of which has been equipped with armor-plating (42), made of a plating material with greater hardness in comparison to the base material, with the armor-plating (42) being segmented and made up of a number of armor-plating segments (44).
摘要:
The invention relates to a heat shield element (1) for lining a combustion chamber wall, to a combustion chamber and to a gas turbine. The heat shield element comprises a hot side (3) that can be exposed to a hot medium (M), a wall side (5) opposite said hot side (3), and a peripheral side (7) adjoining the hot side (3) and the wall side (5) and having a peripheral side surface. Relief slots (9) are introduced into the material in an area of the heat shield element (1) that is susceptible to material cracks induced by thermal stress, thereby limiting crack propagation.