Abstract: A spring seal for sealing in high temperature applications includes a jacket and a spring member disposed within the jacket. The spring member is constructed to control a sealing load or spring rate of the spring seal relative to opposing flanges while the jacket is constructed to provide a sealing surface relative to the opposing flanges. The spring member is manufactured from a cast blade alloy, thereby allowing the spring member to maintain its spring back characteristics at relatively high temperatures of about 1300° F. and greater. Accordingly, the spring member minimizes the formation of a leak path between the spring seal and the opposing flanges. In one embodiment, the spring member is manufactured with a substantially U-shaped cross-section. With such a configuration, the spring seal provides substantially balanced, opposing forces on the jacket to minimize the formation of gaps between the spring seal and the flanges.

Abstract: A turbomachine has a number of interspersed stages of rotor blades and stator vanes. A split case has first and second case sections meeting along a junction extending essentially along a longitudinal first plane. The metallic spring seal extends along the junction. The spring seal may be installed in a remanufacturing of an existing turbomachine.

Abstract: A seal (1) includes a first component (7) and second component (9), the first component including a first material having a high thermal and oxidation and wear resistance, and the second component (9) including a second material that is different from the first material and has a high spring load maintenance. The seal (1) is applied to a combustion chamber for a gas turbine, where the first component (7) extends between the casing wall of the combustion chamber and adjacent liner segments (4). The spring load of the second component (9) provides a seal also in the case of vibrations in a combustion chamber. The lifetime of the seal (1) is increased due to the individual materials, which are optimally chosen for the functions of high thermal and wear resistance and spring load maintenance respectively. The seal is further applied to the sealing between adjacent stationary blade platforms in gas turbines.

Abstract: A seal (10) for sealing joint (12) between a first metal part (14) and a second metal part (16) of an assembly intended for use at an elevated operating temperature (e.g., greater than 1000° C.). The seal (10) comprises a seal body (50) having a first portion (52), a second portion (54), and a flexible intermediate portion (56) therebetween. A first brazed bond (62) attaches the first portion (52) of the seal body (50) to the first part (14) and a second brazed bond (64) attaches the second portion (54) of the seal body (50) to the second part (16). The flexible intermediate portion (56) functions as hinge allowing the first portion (52) and the second portion (54) to move towards or away from each other thereby accommodating relative movement of the first and second metal parts (14, 16).

Abstract: The present invention relates to a sealing body (1) for sealing an outer component (2) with respect to an inner component (3), in particular for a combustion chamber of a gas turbine. The outer component (2) has a passage opening (4), through which the inner component (3) projects out of the outer component (2). In the installed state, the sealing body (1) is arranged in the region of the passage opening (4), surrounds the inner component (3) in a circumferentially continuous manner, bears in a circumferentially continuous manner, by means of an inner sealing zone (7), against an outer sealing surface (6) of the inner component (3) and bears in a circumferentially continuous manner, by means of an outer sealing zone (8), against an inner sealing surface (5) of the outer component (2). The sealing body (1) is produced by deformation from at least one metal sheet that is in strip form and is circumferentially continuous.