Patent Application
20050147335
The present invention is generally related to thrust bearing technology, and is more specifically directed to a stacked foil thrust bearing assembly for use in high speed rotating machinery.
There is a great need for gas turbine engines and auxiliary power units providing improved performance, lower cost, better maintainability, and higher reliability. The Integrated High Performance Turbine Engine Technology program has provided significant advances in compressors, turbines, combustors, materials, generators, and other technologies. In order to make significant improvement in power vs. weight ratio, gas turbine engines and auxiliary power units must operate at higher speed and at higher temperature. In addition, the complicated oil lubrication system must be eliminated to facilitate higher temperature operation, and to reduce weight and cost. Magnetic bearings have shown great promise to meet goals of the Integrated High Performance Turbine Engine Technology program. However, in many applications, use of magnetic bearings is limited due to requirements of auxiliary bearings, cooling methods, weight and cost.
Foil air bearings do provide a promising alternative to magnetic bearings. Foil air bearings are successfully being used in air cycle machines of aircraft environmental control systems. Today, every new aircraft environmental control system, either military or civilian, invariably makes use of foil air bearings. Older aircraft are being converted from ball bearings to foil air bearings. Certain military aircraft air cycle machines used ball bearings up to 1982 and since then, are using foil air bearings. The reliability of foil air bearings in air cycle machines of commercial aircraft has been shown to be ten times that of previously used ball bearings in air cycle machines.
In spite of tremendous success of foil air bearings for air cycle machines, their use for gas turbine engines has been limited. This is due to the fact that gas turbine engines operate at higher temperatures and exhibit higher radial and axial loads. The radial loads are carried by foil journal bearings such as shown in U.S. Pat. No. 3,302,014 and discussed in ASME paper 97-GT-347 (June 1997) by Giri L. Agrawal entitled “Foil Air/Gas Bearing Technology—An Overview.” The axial loads are carried by foil thrust bearings such as shown in U.S. Pat. Nos. 3,382,014 and 4,462,700. In recent years, the load capacity of foil journal bearings has increased to a level which is satisfactory to carry radial loads of a typical gas turbine engine. However, the thrust load capacity requirement of a foil thrust bearing to be used for a gas turbine engine could be as much as four times that supplied by present day thrust bearing technology.
One solution to achieve higher thrust load capacity for a foil thrust bearing in a gas turbine engine is to increase the diameter of the thrust bearing. But larger diameters require greater radial space, increase stresses in the thrust runners, and increase power loss. Load capacity of a foil thrust bearing is also dependent on the flatness of the bearing. As flatness is maximized, load capacity increases. Due to various manufacturing tolerances and constraints, and also due to various operating conditions, keeping the thrust bearing very flat is a difficult task. The problem becomes more difficult as the size, and especially the diameter, of the thrust bearing increases.
The use of foil bearings in turbomachinery has several advantages:
Higher Reliability—Foil bearing machines are more reliable because there are fewer parts necessary to support the rotative assembly and there is no lubrication needed to feed the system. When the machine is in operation, the air/gas film between the bearing and the shaft protects the bearing foils from wear. The bearing surface is in contact with the shaft only when the machine starts and stops. During this time, a polymer coating, such as Teflon®, on the foils limits the wear.
Oil Free Operation—There is no contamination of the bearings from oil. The working fluid in the bearing is the system process gas which could be air or any other gas.
No Scheduled Maintenance—Since there is no oil lubrication system in machines that use foil bearings, there is never a need to check and replace the lubricant. This results in lower operating costs.
Environmental and System Durability—Foil bearings can handle severe environmental conditions such as shock and vibration loading. Any liquid from the system can easily be handled.
High Speed Operation—Compressor and turbine rotors have better aerodynamic efficiency at higher speeds, for example, 60,000 rpm or more. Foil bearings allow these machines to operate at the higher speeds without any of the limitations encountered with ball bearings. In fact, due to the aerodynamic action, they have a higher load capacity as the speed increases.
Low and High Temperature Capabilities—Many oil lubricants cannot operate at very high temperatures without breaking down. At low temperature, oil lubricants can become too viscous to operate effectively. As mentioned above, foil bearings permit oil free operation. Moreover, foil bearings operate efficiently at severely high temperatures, as well as at cryogenic temperatures.
The present invention is directed in one aspect to a stacked foil thrust bearing assembly for use in high speed rotating machines comprising a plurality of thrust runners in adjacently spaced and parallel relationship. Each thrust runner includes an annular-shaped portion having generally opposite axial sides, and a thrust bearing positioned on each of the generally opposite axial sides. Each thrust bearing includes a thrust bearing plate and a spring plate operatively engaging the thrust bearing plate.
The present invention is directed in a second aspect to a stacked foil thrust bearing assembly for use in high speed rotating machines comprising a plurality of thrust runners in adjacently spaced and parallel relationship and having annular thrust-carrying surfaces. The thrust-carrying surfaces of the thrust runners face the same axial direction. A thrust bearing plate is positioned adjacent the annular thrust-carrying surface of each thrust runner. Each thrust bearing plate has two opposite axial sides and including on one axial side a plurality of foils in confronting relationship with the thrust-carrying surface of the thrust runner. A spring plate is positioned adjacent the axial side of each thrust bearing plate opposite the one axial side having the foils. A plurality of springs is included on each spring plate.
The present invention also resides in independent thrust bearing assemblies with individual thrust runners having interlocking fit. The interlocking capability of the bearing assemblies permits adding or subtracting the number of bearings assemblies, including thrust runners and at least two thrust bearings per thrust runner to distribute the load and thrust of the machinery as necessary and as desired.
The benefits of the stacked foil thrust bearing assembly of the present invention include the following:
a) Load capacity is increased without increasing the radial space required for one larger thrust bearing, thus a smaller diameter for the thrust bearings may be maintained.
b) Maximum stress in a stacked foil thrust bearing assembly thrust runner is considerably less than the runner of a larger thrust bearing.
c) The rotating shaft speed of the machine may be increased due to the reduced thrust runner size associated with thrust bearings of smaller diameter.
d) Power loss in multiple thrust bearings combined is less than one larger thrust bearing, because power loss varies as a function of D4, where D is the nominal diameter of the bearing.
e) Multiple thrust bearings will have higher probability of remaining flat and parallel to the thrust runner than one larger diameter bearing, thereby extending the life of the bearings.
The bearing assembly 10 is positioned within a bearing housing 18 and may form part of a rotating shaft coupled to a turbine or a rotor, the shaft extending through the housing 18 along a central axis of rotation 20. The shaft can be coupled to the turbine or rotor by interference fit, tie rod, or other known means. The thrust runners 12a and 12b are disposed within the housing 18 in spaced and parallel relationship to one another. The discussion below focuses on the thrust runner 12a, though the thrust runner 12b has generally the same design and elements. Like reference numerals succeeded by the letters a and b are used to indicate like elements.
Preferably, the thrust runner 12a has an annular-shaped portion 22a extending radially from and circumscribing a hub 24a. The hub 24a preferably forms a section of the shaft so that the thrust runner 12 is capable of rotation around the central axis 20 in coordination with the rotation of the shaft. Alternatively, the hub 24a may be operatively coupled to the shaft. For example, the hub 24a may slide over the shaft so that the associated thrust runner 12a is co-axially aligned with the shaft. The thrust runner 12a may also be a separate piece coupled to a hub 24a or the shaft.
Typically, each thrust runner 12a has first and second opposed axial sides, 26a and 28a respectively, which act as thrust-carrying surfaces. As shown, the first and second sides 26a and 28a are annular thrust-carrying surfaces circumscribing the hub 24a. In a preferred embodiment of the present invention, at least one of the thrust bearings 14a or 16a is provided on a respective axial side 26a and 28a of the thrust runner 12a. However, for unidirectional thrust, only one thrust bearing (e.g., 14a) is needed at one axial side of the thrust runner 12a. The positioning of the thrust bearing 14a with respect to the thrust-carrying surface of the thrust runner 12a—i.e., adjacent one of the axial sides 26a or 28a—is determined based on the direction of thrust and how the distribution of the axial loads will be best maximized. Where multiple thrust runners are stacked in adjacently spaced and parallel relationship, the thrust-carrying surface of each thrust runner will be facing the same axial direction.
The thrust bearings 14a and 16a, and 14b and 16b of the present invention are shown more particularly in
As shown in
Preferably, the thrust bearing 14a is centered on and is generally symmetric about the central axis 20. Each thrust runner 12a and its respective axially disposed thrust bearings 14a and 16a support and transmit the axial load of the rotating machinery through the assembly in a distributed fashion. Where thrust bearings are provided on both axial sides of the thrust runner 12a, both sides act as thrust-carrying surfaces. The thrust bearing on one axial side of a thrust runner (e.g., thrust bearing 14a), designated a clockwise thrust bearing, supports and distributes axial load in one direction, while the thrust bearing on the opposed axial side (e.g., thrust bearing 16a), designated a counter-clockwise thrust bearing, supports and distributes axial load in the other direction. The clockwise or counter-clockwise designations are defined when viewing the thrust bearing along the central axis 20 facing the thrust runner 12a.
In order to meet high load capacity requirement of a rotating machine, such as a gas turbine engine, two or more thrust runners, each with corresponding thrust bearings flanking both axial sides thereof, are used to share the loads. The hub 24a for the thrust runner 12a may be provided with at least one interlocking or mating surface 42 to facilitate the stacking and alignment of the thrust runner 12a with additional thrust runners, such as thrust runner 12b in
The top foils 32a on the thrust bearing plate 30a are typically made from flexible steel foil, such as Inconel®, and have a thickness between about 0.003 inches to about 0.015 inches. The top foils 32a are commonly secured to the axial side of the thrust bearing plate 30a facing the thrust runner 12a, and are preferably welded along a leading edge 46a of the foils 32a to the thrust bearing plate 30a at circumaxial positions thereabout, while a trailing edge 44a of the foils 32a is free to flex. The leading edge 46a of each top foil 32a is defined with respect to the direction of rotation of the shaft relative to the top foils 32a. The top foils 32a are thus compliant with the thrust runner 12a during high-speed shaft rotation and, in conventional fashion, form a hydrodynamic lift to support the axial load. A polymer coating, such as Teflon®, is provided on the exposed outer face of the top foils 32a to protect them during start-up until air or gas film at the interface between the foils 32a and the thrust runner 12a takes over. Preferably, the top foils 32a are sector-shaped so as to maximize their compliance while the respective thrust runner 12a is rotating about the central axis 20.
Preferably, each spring plate operatively engages an adjacent thrust bearing plate within the housing 18. While the thrust bearing plate 30a and the spring plate 34a could be combined into one plate with the top foils 32a on one side and the springs 36a on the other side, the practice of using separate plates, as shown, is preferred. The top foils 32a are located on the axial side of the thrust bearing plate 30a opposite from the spring plate 34a. Preferably, the leaf springs 36a are disposed on the axial side of the spring plate 34a facing the housing 18, opposite from the thrust bearing plate 30a. The leaf springs 36a are usually welded to the spring plate 34a. While a specific design for the leaf springs 36a is shown, various leaf spring or flat spring designs may be used on the spring plate 34a, without departing from the broader aspects of the present invention. The preferred axial positioning and arrangement of the thrust bearing plate 30a, the top foils 32a, the spring plate 34a and the leaf springs 36a of the thrust bearing 14a with respect to the thrust runner 12a, as well as the similar components for thrust bearing 16a, and also thrust bearings 14b and 16b with respect to thrust runner 12b, can be more clearly seen in
Assuming that the thrust runners 12a and 12b and the respective thrust bearings 14a, 16a and 14b, 16b therefor are positioned along the central axis 20 within prescribed tolerances relative to the housing 18, the compliance of the top foils and springs used therewith ensures that the thrust loads of the turbine or rotor are distributed evenly between the plurality of stacked thrust bearings 14a, 16a and 14b, 16b. Consequently, the load-carrying capacity of the thrust bearing assembly of the present invention is increased by multiples over the current state of the technology using a single thrust runner and foil bearings.
The foregoing description of embodiments of the present invention has been presented for the purpose of illustration and description, and is not intended to be exhaustive or to limit the present invention to the form disclosed. For example, although the illustrated embodiments show only two stacked thrust runners and associated foil thrust bearings in an assembly, it should be clear that three or more thrust runners with associated foil thrust bearings can be stacked in an assembly for increased thrust load capacity. As will be recognized by those skilled in the pertinent art to which the present invention pertains, numerous changes and modifications may be made to the above-described embodiments without departing from the broader aspects of the present invention.
This application claims the benefit of U.S. Provisional Application 60/415,907, filed Oct. 3, 2002, which is incorporated herein by reference.
| Number | Date | Country | |
|---|---|---|---|
| 60415907 | Oct 2002 | US |
