THERMALLY ADAPTIVE BEARING SLEEVE

Abstract

A component of a gas foil bearing, having a plurality of material layers forming a composition gradient that defines a first coefficient of thermal expansion (CTE) and a second CTE that differs from the first CTE, wherein: the plurality of material layers include at least two dissimilar metals, plastics, or fiber filled metals or plastics, that are layered on top of each other; when the component is subject to heating, the component changes from a first shape to a second shape; and the component is a bearing sleeve.

Claims

1. A component of a gas foil bearing, comprising: a plurality of material layers forming a composition gradient that defines a first coefficient of thermal expansion (CTE) and a second CTE that differs from the first CTE, wherein: the plurality of material layers include at least two dissimilar metals, plastics, or fiber filled metals or plastics, that are layered on top of each other; when the component is subject to heating, the component changes from a first shape to a second shape; and the component is a bearing sleeve.

2. The component of claim 1, wherein the first shape is a curved triangle.

3. The component of claim 2, wherein the second shape is circular.

4. The component of claim 3, wherein the plurality of layers include: a first layer that forms a body of the component; and a second layer has a same size and shape as the first layer and extends about an exterior side or an interior side of the first layer.

5. The component of claim 3, wherein the plurality of layers include: a first layer that forms a body of the component; and a second layer that extends about a portion of an exterior side or an interior side of the first layer.

6. The component of claim 5, wherein: when the component forms the curved triangle, portions of the first layer define corners of the curved triangle; and the second layer forms discrete segments that are located at the corners of the curved triangle.

7. The component of claim 4, wherein the second layer has a thickness of 10 microns or less.

8. The component of claim 5, wherein the second layer has a thickness of 10 microns or less.

9. A gas foil bearing, comprising: the component of claim 1; a bump foil surrounded by the component; and a top foil surrounded by the bump foil.

10. The bearing of claim 9, further comprising: a journal shaft surrounded by the top foil and supported by the bearing.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:

[0014] FIG. 1 shows an aircraft according to an embodiment;

[0015] FIG. 2 shows a gas foil bearing (GFB) that may be utilized in the aircraft, according to an embodiment;

[0016] FIG. 3 shows a bearing sleeve of the GFB in one shape state, when the GFB is relatively warm;

[0017] FIG. 4 shows the bearing sleeve in a second shape state, when the GFB is relatively cold;

[0018] FIG. 5 shows a detail of the bearing sleeve, utilizing material layers having different coefficients of thermal expansion (CTEs) that result in the predetermined shape states;

[0019] FIG. 6 shows an element that is equivalent to the sleeve configurations disclosed herein, with two material layers having different CTEs, at a temperature T1;

[0020] FIG. 7 shows the structure of FIG. 56 at a temperature T2>T1; and

[0021] FIG. 8 shows an element similar to that of FIG. 6 at a temperature T2>T1, where a material interface allows free slip between layers, such the layers extend at different rates upon being heated.

DETAILED DESCRIPTION

[0022] A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.

[0023] FIG. 1 shows an aircraft 1 having a fuselage 2 with a wing 3 and tail assembly 4, which may have control surfaces 5. The wing 3 may include an engine 6, such as a gas turbine engine, and an auxiliary power unit 7 may be disposed at the tail assembly 4. The aircraft 1 may have an air cycle machine 10.

[0024] Turning to FIG. 2, rotating parts such as a journal shaft (or shaft) 100 may rotate within a gas foil bearing (GFB) 110. The GFB 110 includes a bearing sleeve 120, or bushing, that may be cylindrical. The bearing sleeve 120 may surround a bump foil 130, which may be ring shaped with an undulating profile. The bump foil 130 may surround a top foil 140, which also may be ring shaped and have a cylindrical profile. A predetermined gap 150 may be defined between the top foil 140 and the shaft 100, which may be separated by a layer of air film during rotation of the shaft 100.

[0025] FIG. 3 schematically shows the shape of the bearing sleeve 120 at a first temperature T1. FIG. 4 shows the shape of the bearing sleeve 120 at a second temperature T2<T1. That is, in a relatively cold state of the GFB 110, the sleeve 120 has a curved triangular shape so that there are at least three points of contact 155A-155C between the GFB 110 and the internal shaft 100 (e.g., a first shape state). When the temperature of the GFB 110 is elevated, e.g., during steady-state operation, the shape of the sleeve 120 is round (e.g., a second shape state).

[0026] To obtain the shape changes shown in FIGS. 3 and 4, as shown in FIG. 5, the bearing sleeve 120 may be additively manufactured with a plurality of dissimilar materials, including dissimilar metals or thermoplastic polymers which may be filled with dissimilar fibers. With the materials, the sleeve 120 forms a composition gradient that defines a first coefficient of thermal expansion (CTE) and a second CTE that differs from the first CTE. With the composition gradient, the different shapes shown in FIGS. 3 and may be obtained at different operating temperatures of the GFB 110.

[0027] More specifically the sleeve 120 has a first layer 158 of a first material forming a body 160 of the bearing sleeve 120. The first layer 158 may have a first coefficient of thermal expansion (CTE). By utilizing additive manufacturing, a second layer 170 of a second material may be provided around a portion the body 160 or the entire body 160 of the bearing sleeve 120, i.e., having a same size and shape as the first layer 158. The second layer 170 may be 10 microns thick. The second layer 170 may be a different material than the first layer 158, having a second CTE that differs from the first CTE to form a CTE gradient.

[0028] In one embodiment, the second layer 170 is distributed only at predetermined locations 180, such as three portions 180A-180C of the first layer 158, which are circumferentially distributed around the body 160 of the bearing sleeve 120. These locations 180A-180C form corners of the curved triangular shape shown in FIG. 4. In one embodiment the second layer 170 is formed on an exterior side 160A of the bearing sleeve body 160, though the second layer 170 may be formed on an interior side 160B of the bearing sleeve body 160.

[0029] FIGS. 6 and 7 show a structural element 248 that is equivalent to the layers shown in FIG. 6. Specifically, first and second layers 200, 210, which may be dissimilar metals, thermoplastic polymers, and which may be filled with dissimilar fibers, to provide dissimilar CTEs. The layers 200, 210 are at a temperature T1 in FIGS. 6, and T2 that is greater than T1 in FIG. 7. The controlled thermal expansion shown in FIG. 7 results from the layers 200, 210 being integrally connected. That is, the first and second layer 200, 210 bend together in a predictable and controlled way. That is, the controlled thermal expansion of the first and second layers 200, 210 provides the desired shape change of the structural element 248. FIG. 8 shows an element 405 that is similar to that of FIG. 6 at a temperature T2>T1, where a material interface allows free slip between layers 450, 460, such the layers 450, 460 extend at different rates upon being heated, rather than deforming as shown in FIG. 7.

[0030] Benefits of a thermally adaptive bearing sleeve 120 that changes shape as shown in FIGS. 3 and 4 include a reduction of non-uniform or undesired deformation that may otherwise occur with temperature gradients that are induced throughout the operation of the GFB 110. That is, the embodiments provide a GFB 110 that has an optimized stiffness over substantially an entire range of operation of the GFB 110. The GFB 110 that deforms as shown in FIGS. 3-4 may increase the bearing capacity, reduce startup draft, increase durability, provide improved modal stability, and provide an increased capacity.

[0031] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms a, an and the are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms comprises and/or comprising, when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.

[0032] Those of skill in the art will appreciate that various example embodiments are shown and described herein, each having certain features in the particular embodiments, but the present disclosure is not thus limited. Rather, the present disclosure can be modified to incorporate any number of variations, alterations, substitutions, combinations, sub-combinations, or equivalent arrangements not heretofore described, but which are commensurate with the scope of the present disclosure. Additionally, while various embodiments of the present disclosure have been described, it is to be understood that aspects of the present disclosure may include only some of the described embodiments. Accordingly, the present disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.