Turbine leaf seal mounting with headless pins

A gas turbine engine has a leaf seal assembly and further includes an arcuate segment (32) having an arcuate band segment with a tab (53) and an arcuate rail segment spaced axially apart from the tab and located along an axial end of the band segment. The tab and the arcuate rail segment extend radi...

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Bibliographische Detailangaben
Hauptverfasser:	HEFFRON, TODD S, HEYWARD, JOHN P, ACKERMAN, ROBERT I, MORGAN, OLIVE A, WIENHOLTS, ERIC J
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CYLINDERS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PISTONS SEALINGS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine has a leaf seal assembly and further includes an arcuate segment (32) having an arcuate band segment with a tab (53) and an arcuate rail segment spaced axially apart from the tab and located along an axial end of the band segment. The tab and the arcuate rail segment extend radially away from the band segment. A leaf seal (52) and a spring (56) are disposed within the space (58) between the tab and the rail segment to bias the leaf seal against the aft rail (48). The spring has a spring aperture (75) entirely therethrough, the leaf seal (52) has a seal aperture (74) entirly therethrough, and a headless pin (78) is disposed in the apertures such that the leaf seal and the spring are radially restrained by the pin (78). An axial restraining means prevents axial movement of the pin (78) out of the tab aperture (70).