Dresser-Rand Company

United Technologies Corporation

Siemens Energy, Inc.

Griffin, Daniel J.

Daniel J Griffin

Joseph T Caprario

William C Maier

A seal apparatus for a casing of a turbomachine. The seal apparatus may include an annular body having first and second annular body portions and an appendage. The second annular body portion may extend axially from the first annular body portion and may have an outer annular surface radially offset from an outer annular surface of the first annular body portion. The appendage may extend axially from the first annular body portion and may have an outer annular surface and an inner annular surface. The inner annular surface of the appendage and the outer annular surface of the second annular body portion may define an annular cavity therebetween, and at least a portion of the appendage may be configured to be displaced radially outward in order to maintain contact with first and second inner cylindrical surfaces of the casing during radial expansion of the casing.

Seal apparatus for a turbomachine casing

A shaft of a compressor may include a first shaft section defining a first cavity axially extending therein and a second shaft section defining a second cavity axially extending therein. A plurality of inlet holes may be defined on an outer surface of the first shaft section, and a plurality of outlet holes may be defined on an outer surface of the second shaft section. The plurality of inlet holes may be in fluid communication with the first cavity and the plurality of outlet holes may be in fluid communication with the second cavity. The first cavity and the second cavity may form a passageway fluidly coupling the plurality of inlet holes and the plurality of outlet holes.

Compressor having hollow shaft

An annular seal is provided for use in a turbomachine. The annular seal may form a generally rectangular cross-section and may include an outer radial surface forming an outer sealing surface and defining at least one annular groove and a plurality of slots spaced circumferentially about the outer radial surface. Each slot may have an end terminating in the at least one annular groove. The annular seal may also include a first axial sidewall forming a sidewall sealing surface and a recessed portion and a second axial sidewall opposing the first axial sidewall. At least one annular groove and the plurality of slots may be configured to maintain a low pressure environment across at least a portion of the outer radial surface. The second axial sidewall, the recessed portion, and the inner radial surface may be configured to maintain a high pressure environment there across during operation of the turbomachine.

Seal for a high-pressure turbomachine

Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

Gas turbine systems involving rotor bayonet coverplates and tools for installing such coverplates

A bearing assembly support and adjustment system includes an annular support device and an annular adjustment sleeve. The annular support device has a support device outer circumferential surface located about a first axis and a support device inner circumferential surface located about a second axis spaced apart from the first axis. The annular adjustment sleeve has an adjustment sleeve outer circumferential surface located about a third axis and an adjustment sleeve inner circumferential surface located about a fourth axis spaced apart from the third axis. The annular adjustment sleeve is coupled to the annular support device with the adjustment sleeve outer circumferential surface located immediately adjacent the support device inner circumferential surface.

Bearing assembly support and adjustment system

Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates

A closure device for a casing having at least one access opening wherein the closure device includes a cover member movably disposed within an interior chamber of the casing so as to be slidably displaceable along or in the direction of a casing central axis between an open and a closed position, the cover member being spaced at least partially axially from the access opening in the open position so as to permit access to the interior chamber and generally extending across and substantially obstructing the at least one access opening in the closed position.

Growing community of inventors

Enfield, CT, United States of America

Daniel J Griffin