BLADE TO STATOR HEAT SHIELD INTERFACE IN A GAS TURBINE

The invention relates to a blade to stator heat shield interface in a gas turbine. A gas turbine unit has an axis (A) parallel to the main gas flow (M), the gas turbine unit comprising: - a blade (1)having a tip (2); - a stator heat shield (3) having an inner surface (4) facing the blade tip (2); wh...

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Bibliographische Detailangaben
Hauptverfasser:	GUENTER FILKORN, BEAT VON ARX, MARTIN SCHNIEDER, FRANCESCO GARBUGLIA, MARCEL KOENIG
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a blade to stator heat shield interface in a gas turbine. A gas turbine unit has an axis (A) parallel to the main gas flow (M), the gas turbine unit comprising: - a blade (1)having a tip (2); - a stator heat shield (3) having an inner surface (4) facing the blade tip (2); wherein the inner surface (4) of the stator heat shield (3) and the blade tip (2) define a variable clearance depending on the applied thermal condition; wherein the blade tip (2) is configured to have a cylindrical shape along the axial direction in a hot running condition starting from a conical shape along the axial direction in a cold starting condition. 本发明涉及燃气涡轮中的叶片与定子隔热罩分界。具体而言，种燃气涡轮单元具有平行于主要气体流(M)的轴线(A)，该燃气涡轮单元包括：叶片(1)，其具有末梢(2)；定子隔热罩(3)，其具有面向叶片末梢(2)的内表面(4)；其中，定子隔热罩(3)的内表面(4)和叶片末梢(2)取决于应用的热条件限定可变间隙；其中，叶片末梢(2)构造成从在冷起动条件中沿着轴向方向的锥形形状开始在热运行条件中具有沿着轴向方向的圆柱形形状。