Abstract: Embodiments of the invention relate to a system and method for controlling the size of gaps in a turbine engine. In many instances, it is desirable to minimize the size of the gaps between neighboring rotating and stationary components in a turbine engine, such as between a disc cover plate and a proximate pre-swirler. According to embodiments of the invention, each component can be provided with a sealing surface. The sealing surfaces can be angled relative to the axis of rotation. The sealing surfaces are spaced from each other so as to form a gap therebetween. The sealing surfaces may or may not be substantially parallel. As a result of such configuration, the size of the gap can be controlled by axial and radial movement of the components. For example, the gap between the cover plate and the pre-swirler can be adjusted by axially movement of the rotor.

Abstract: A seal usable in a turbine engine for sealing a high pressure gas region from a low pressure gas region. The seal seals gaps between a rotatable body and a stationary body by creating forces opposing flow from the high pressure region to the low pressure region. During turbine engine operation, the seal creates aerodynamic forces that substantially prevents leakage of gases from a high pressure region to a low pressure region. The seal may be formed from a plurality of blades aligned in one or more rows and extending from a rotatable body towards a stationary body of the turbine engine to be in close proximity to the stationary body. The seal may also include a plurality of blades aligned in one or more rows and extending from the stationary body towards the rotatable body to be within close proximity of a surface of the rotatable body.