Patent Grant
9840937
1. Field
The present application relates to gas turbines, and more particularly to a casing arrangement to improve component stiffness in a gas turbine, a casing arrangement to reduce operative vibrations, as well as a method to reduce critical panel mode response in a gas turbine casing and a method to reduce operative vibrations in a gas turbine casing.
2. Description of the Related Art
The turbine exhaust cylinder and the turbine exhaust manifold are coaxial gas turbine casing components connected together establishing a fluid flow path for the gas turbine exhaust. The fluid flow path includes an inner flow path and an outer flow path defined by an inner diameter delimiting an outer surface of the inner flow path and an outer diameter delimiting an inner surface of the outer flow path, respectively. Struts are arranged within the fluid flow path and serve several purposes such as supporting the inner and outer surfaces of the flow path and providing lubrication for the turbine and rotor bearing. The exhaust flow around the struts causes vibrations of the inner and outer diameter of the turbine exhaust cylinder and the turbine exhaust manifold due to vortex shedding. Vortex shedding are vibrations induced as the exhaust flows past the struts, where the struts partially obstruct the flow of the exhaust in the inner flow path. These vibrations are a potential contributor to damage occurring to the flow path of the turbine exhaust manifold and the turbine exhaust cylinder. This damage to the casing components may require early replacement or repair.
Briefly described, aspects of the present disclosure relates to a casing arrangement to reduce operative vibrations in a gas turbine and a method to reduce vibrations in a gas turbine casing.
A first aspect of provides a casing arrangement to improve component stiffness in a gas turbine component. The casing arrangement includes a turbine exhaust cylinder, a turbine exhaust manifold connected to the turbine exhaust cylinder establishing a fluid flow path, a damping blanket effective to damp vibrational amplitude and a constraining layer effective to keep the damping blanket in contact with the inner flow path. The fluid flow path includes an inner and an outer flow path.
A second aspect of provides a method to reduce vibrations in a gas turbine casing. The method includes disposing a damping blanket against a flow path of the gas turbine and coupling the plurality of stiffening ribs to the damping blanket. The flow path is defined by an inner and an outer flow path and is bounded radially inward by an outer surface of the inner flow path and radially outward by an inner surface of the outer flow path. Vibrations in the turbine exhaust cylinder and turbine exhaust manifold are reduced by compression of the damping blanket and the stiffness of the plurality of stiffening ribs.
To facilitate an understanding of embodiments, principles, and features of the present disclosure, they are explained hereinafter with reference to implementation in illustrative embodiments. Embodiments of the present disclosure, however, are not limited to use in the described systems or methods.
The components and materials described hereinafter as making up the various embodiments are intended to be illustrative and not restrictive. Many suitable components and materials that would perform the same or a similar function as the materials described herein are intended to be embraced within the scope of embodiments of the present disclosure.
Damage to gas turbine casing components is an issue that may be caused by vibrations within the inner and outer flow path of the gas turbine exhaust system. The vibrations may be driven by insufficient component stiffness of the turbine exhaust cylinder and/or the turbine exhaust manifold. The stiffness of a component is defined as the rigidity of the component or how well it resists deformations in response to applied forces. Insufficient component stiffness may allow vibrations such as panel modes and/or critical modes to be generated and stay in resonance along with vibrations created by the exhaust flow. Panel modes are mode shapes of panels. Critical modes are mode shapes that couple with the forcing function or energy input and are especially problematic because they may create damage to the casing components, particularly to the flow path of the gas turbine.
One approach to avoid component damage to the casing components caused by vibrations would be to change the vibration frequency away from the critical frequency or resonant frequency. This may be done according to the principle describing natural frequency,
where
fa=natural frequency in hertz (cycles/second)
k=stiffness of the spring (Newtons/meter or N/m)
m=mass (kg)
In the gas turbine casing components, the turbine exhaust cylinder and turbine exhaust manifold, the critical frequency typically lies in the range, 120-150 Hz. According to the natural frequency principle, by changing the mass and/and or the stiffness of a component, the natural frequency may be changed. It is from this reasoning that in an embodiment it is proposed to add stiffening ribs to increase the stiffness and change the natural frequency of the casing components outside the critical range to sufficiently avoid a dynamic response issue.
In another embodiment, another approach to avoid component damage to the casing components caused by vibrations would be to introduce a damping mechanism to damp the problematic vibrations and transfer the energy associated with these vibrations to heat energy. The damping mechanism may reduce the amplitude of the vibrations lessening their severity and capacity to damage the casing components. Existing insulation positioned on the inner surface of the inner flow path used to insulate components outside of the flow path against the heat of the flow path may also be used to provide the damping mechanism. The layers of insulation may be preloaded, or compressed, an amount to provide sufficient damping to damp the unwanted vibrations while not disintegrating the insulation.
In the shown embodiment, stiffening ribs (50) are coupled to the inner surface (75) of the inner flow path and are positioned axially along the flow path. As previously stated, changing the stiffness of a component, in this case the flow path of the exhaust system of a gas turbine, may be used to change the vibration frequency away from the critical frequency. Illustrated in
The further planar portion (140) of the embodiment shown in
A cross sectional view of the L-shaped stiffening rib (50) of
An embodiment of a radial threaded rod (100) and its corresponding washer (110) is shown in
As previously mentioned, the plurality of stiffening ribs (50) may be coupled to the surface of the flow path using a plurality of coupling holes (150, 160). The positioning of the coupling holes (150, 160) is a function of the geometry of the gas turbine exhaust system and the location of the stiffening ribs (50). In the embodiment of
Referring to
In order to minimize the thermal gradient between the flow path struts (40) and the stiffening ribs (50), the stiffening ribs (50) are disposed in relatively cool locations against the surface of the flow path. A high thermal gradient between the flow path struts (40) and the stiffening ribs (50) may be damaging to the stiffening ribs causing material degradation.
Each stiffening rib (50) comprises an arcuate segment with a plurality of coupling holes (150, 160) as described previously and may be positioned against the flow path in the circumferential and axial directions via the central coupling hole (150). Welded radial threaded rods (100) may then be inserted into the coupling holes (150, 160) such that the welded portion of the radial threaded rod (100) is welded to both the stiffening rod (50) and to the inner surface (75) of the inner flow path. The radial threaded rod (100) would then be secured with a hex nut (120) and washer (110).
Several stiffening ribs (50) may be coupled circumferentially around the inner surface of the inner flow path (75) creating a continuous stiffening hoop. Adjacent stiffening ribs (50) may be attached together using a bolted connection plate (60). The bolted connection plate (60) may be attached to each stiffening rib (50) via a plurality of connection holes (170) in the stiffening rib (50). Additionally, several continuous stiffening hoops may be disposed in different axial positions along the surface of the flow path in order to address specific panel modes and vibratory responses within the turbine exhaust system (10).
The casing arrangement and corresponding method provides a way to increase stiffness in the critical areas of the turbine exhaust system flow path and decrease the critical mode response without compromising the components' structural integrity. Additionally, the stiffening rib coupling scheme is retrofittable and could be installed on existing gas turbines without significant modifications to the existing hardware.
In another embodiment, a casing arrangement including a damping blanket and a constraining layer is used to improve stiffness in a gas turbine, specifically the gas turbine exhaust system (10).
The damping blanket (310) combined with the constraining layer (350) introduces a frictional damping mechanism which damps the vibrations and transfers the energy of the excessive vibrations into heat energy. The bushing (360) helps to compress the layers of insulation to a desired thickness. Friction between the layers of insulation and the inner surface of the inner flow path (75) due to the compression creates the frictional damping mechanism that converts dynamic energy to heat.
The layers of insulation used may be ceramic insulation. As an example, the thickness of the layers may be approximately 75 mm. After being compressed using the bushing (360), the thickness of the layers may be approximately 50 mm, a 33% compression. Ceramic insulation is currently used in the gas turbine exhaust system (10) to keep the internal cavity and the bearing cool. However, the layers of insulation used is not limited to ceramic insulation. Other types of insulation such as foam and metal encapsulated may be used provided that the insulation type could withstand temperatures in the ranges of 300° C. to 600° C. which is a typical temperature range that exists in the gas turbine exhaust system.
Referring to the FIGS., specifically
The damping blanket (310) may be comprised of a plurality of layers of insulation (310) including an outermost layer and an innermost layer. The outermost layer may be coupled to the inner surface of the inner flow path (75) as shown in the illustrated embodiment. The plurality of stiffening ribs (350) are coupled to the innermost layer of insulation such that the insulation is disposed between the inner surface of the inner flow path (75) and the stiffening ribs (350). One or more bushings (360) may be disposed each within an opening in the insulation (310).
Each stiffening rib (350) comprises an arcuate segment with a plurality of coupling holes as described previously and may be positioned against the innermost layer of insulation in the circumferential and axial directions using the central coupling hole. In the illustrated embodiment, the stiffening rods (100) are circumferentially coupled to the innermost layer of insulation. Radial threaded rods (100) may then be inserted through coupling holes (150, 160) in the stiffening rib (350) and into an opening in the bushing (360). The welded portion of the radial threaded rod is welded to the inner surface of the inner flow path (75). The radial threaded rod (100) would then be secured with a hex nut (120) and washer (110).
Similarly to the embodiment having the plurality of stiffening ribs (350) coupled directly to the inner surface of the inner flow path (75), several stiffening ribs (350) may be coupled circumferentially around the innermost layer of insulation creating a continuous stiffening hoop. Adjacent stiffening ribs may be attached together using a bolted connection plate (60). The bolted connection plate (60) may be attached to each stiffening rib (350) via a plurality of connection holes (170) in the stiffening rib. Additionally, several continuous stiffening hoops may be disposed in different axial positions along the surface of the flow path in order to address specific panel modes and vibratory responses within the turbine exhaust system.
While embodiments of the present disclosure have been disclosed in exemplary forms, it will be apparent to those skilled in the art that many modifications, additions, and deletions can be made therein without departing from the spirit and scope of the invention and its equivalents, as set forth in the following claims.
| Number | Name | Date | Kind |
|---|---|---|---|
| 8894359 | Munshi | Nov 2014 | B2 |
| Entry |
|---|
| Nelson Stud Welding, Inc., “Stud Welding—CPL Partially Threaded Studs”, Nelson Stud Welding, Inc., Standard Stock Products Catalog, Feb. 2004, p. 22. |
| Number | Date | Country | |
|---|---|---|---|
| 20160201506 A1 | Jul 2016 | US |
