Patent Grant
10704560
Centrifugal impellers are used in turbine machines, such as a centrifugal pump or a centrifugal compressor, to provide high pressure working fluid to a combustor. In some turbine machines, for example, a centrifugal compressor may be used as the final stage in a multi-stage high-pressure gas generator.
An annular shroud 120 encases the plurality of blades 112 of the centrifugal impeller 111. The gap between a radially inner surface 122 of shroud 120 and the impeller blade tips 113 is the blade tip clearance 140 or clearance gap. Shroud 120 may be coupled to a static portion of the engine casing 131 directly or via a first mounting flange 133 and second mounting flange 135.
Gas turbine engines having centrifugal compressors 100 such as that illustrated in
It is known in the art to dynamically change blade tip clearance 140 to minimize rub while also reducing leakage of the working fluid around the blade tips 113. Several actuation systems for adjusting blade tip clearance 140 during engine operation have been developed. These systems often include complicated linkages, contribute significant weight, and/or require a significant amount of power to operate. Thus, there continues to be a demand for advancements in blade clearance technology to minimize rub while avoiding leakage.
According to some aspects of the present disclosure, a centrifugal impeller shroud assembly has a dynamically moveable impeller shroud for encasing a rotatable centrifugal impeller and resolving misalignment between the impeller shroud and the rotatable centrifugal impeller. The assembly comprises a static casing, an impeller shroud, a shroud arm, and a thermal member. The impeller shroud faces the rotatable centrifugal impeller and extends from an inlet to an outlet. The shroud arm is coupled between the casing and the impeller shroud. The shroud arm comprises a flexible portion, with the shroud arm and impeller shroud at least partially defining a first cavity in fluid communication with the inlet and a second cavity in fluid communication with the outlet. The flexible portion is configured to flex responsive to a differential pressure between the first cavity and the second cavity. The thermal member is coupled to the impeller shroud proximate the outlet. The thermal member has a coefficient of thermal expansion (CTE) lower than the CTE of the shroud.
In some embodiments flexion of the flexible portion of the shroud arm effects axial movement of the impeller shroud. In some embodiments the flexible portion of the shroud arm comprises a U-shaped cross section when viewed normal to an axis of rotation of the centrifugal impeller. In some embodiments a concave surface of the U-shaped cross section is in communication with the second cavity.
In some embodiments the shroud arm is coupled to the impeller shroud at a knee of the shroud. In some embodiments the second cavity is exposed to fluid at the impeller discharge pressure. In some embodiments the first cavity is exposed to fluid at the impeller inlet pressure.
In some embodiments the thermal member effects deflection of the shroud proximate the outlet, the deflection responsive to changes in temperature. In some embodiments movement and deflection of the shroud resolves misalignment between the shroud and the centrifugal impeller. In some embodiments the thermal member has a CTE substantially the same as the CTE of the centrifugal impeller. In some embodiments the assembly further comprises a static member positioned to limit aft movement of the shroud.
According to another aspect of the present disclosure, a centrifugal impeller shroud assembly has a dynamically moveable impeller shroud for encasing a rotatable centrifugal impeller and resolving misalignment between the shroud and the rotatable centrifugal impeller. The assembly comprises a shroud, a thermal member, and a shroud arm. The shroud extends between a forward end proximate an inlet and an aft end proximate an outlet. The thermal member is coupled to the shroud proximate the aft end of the shroud. The thermal member comprises a material having a lower coefficient of thermal expansion (CTE) than the material of the shroud to thereby effect deflection of the aft end of the shroud responsive to changes in temperature. The shroud arm is coupled between the shroud and a static casing. The shroud arm comprises a flexible portion that flexes responsive to a pressure differential across the shroud arm to thereby effect axial movement of the shroud responsive to changes in the differential pressure across the shroud arm.
In some embodiments the shroud comprises an impeller-facing member and a coupling member extending forward from the impeller-facing member, the thermal member being coupled to the shroud via the coupling member. In some embodiments the assembly further comprises a static member positioned to limit aft movement of the aft end of the shroud. In some embodiments the thermal member comprises one or more of nickel alloy, Inconel, titanium, or low-a steel.
In some embodiments the shroud arm is coupled to the shroud approximate a midpoint between the forward end and the aft end. In some embodiments the flexible portion of the shroud arm comprises a U-shaped cross section when viewed normal to an axis of rotation of the centrifugal impeller. In some embodiments movement and deflection of the shroud resolves misalignment between the shroud and the centrifugal impeller.
According to yet another aspect of the present disclosure, a method of dynamically changing the shape of a shroud encasing a centrifugal impeller is presented. The shroud comprises a boundary member extending from an inlet end to a discharge end. The method comprises deflecting the discharge end of the boundary member responsive to changes in the temperature of the fluid at the discharge end by mounting a thermal member to the shroud proximate the discharge end of the boundary member, the thermal member comprising a material having a coefficient of thermal expansion (CTE) that is lower than the CTE of the boundary member; and axially moving a knee portion of the boundary member responsive to changes in the differential pressure between the fluid at the inlet end and the fluid at the discharge end of the boundary member by coupling the shroud to a static casing via a shroud arm, the shroud arm having a flexible portion configured to flex responsive to a differential pressure between the inlet end and the discharge end of the boundary member.
In some embodiments the method further comprises selecting the material of the thermal member to thereby effect thermal deflection of the discharge end of the boundary member in a manner similar to the thermal expansion of the discharge end of the centrifugal impeller during operation of the centrifugal impeller. In some embodiments the method further comprises selecting the flexion of the flexible portion of the shroud arm to thereby effect axial movement of the knee portion of the boundary member in a similar manner to the axial movement of the centrifugal impeller responsive to changes in the differential pressure from the inlet end to the discharge end of the centrifugal impeller during operation of the centrifugal impeller.
The following will be apparent from elements of the figures, which are provided for illustrative purposes.
While the present disclosure is susceptible to various modifications and alternative forms, specific embodiments have been shown by way of example in the drawings and will be described in detail herein. It should be understood, however, that the present disclosure is not intended to be limited to the particular forms disclosed. Rather, the present disclosure is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the disclosure as defined by the appended claims.
For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments in the drawings and specific language will be used to describe the same.
The present disclosure is directed to maintaining clearance between a centrifugal impeller and a shroud. The present disclosure pertains to many applications of a centrifugal impeller and shroud, such as a centrifugal pump or a centrifugal compressor in a gas turbine engine.
Maintaining a sufficient clearance gap 140 during operation of the centrifugal compressor 100 is challenging not only due to operational transients, but also because the centrifugal impeller 111 (including blades 112) tends to alter its shape during operation.
During operation, the exducer 117 (or outlet end) of the centrifugal impeller 111 curls axially forward from the non-operating position of the exducer 117. This deflection is caused by thermal, mechanical, and pressure loading of the centrifugal impeller 111. The deflection creates a misalignment between the centrifugal impeller 111 and shroud 120.
Existing systems that address the control of an impeller shroud fail to resolve the misalignment between the shroud 120 and centrifugal impeller 111 resulting from operational deflection of the centrifugal impeller 111. As discussed above with respect to
The present disclosure is thus directed to systems and methods of passively maintaining a clearance gap between a shroud and the rotatable blades of a centrifugal impeller, to include maintaining the clearance gap despite deflection of the centrifugal impeller during operation. More specifically, this disclosure presents systems having a thermal member coupled to the aft end of the shroud and a flexible shroud arm extending between a static case and the shroud. As described below, the thermal member and flexible shroud arm cooperate to passively position the shroud relative to the centrifugal impeller to maintain the clearance gap and resolve potential misalignment. This disclosure also presents methods of maintaining a clearance gap and resolving potential misalignment between a centrifugal impeller and shroud.
A dynamically moveable shroud 320 extends between an inlet (forward) end 324 and a discharge (aft) end 326. The forward end 324 is proximate the compressor inlet 346 and the aft end 326 is proximate the compressor outlet 347. A central portion of the shroud 320 is referred to as the knee 328 or knee portion. The shroud 320 comprises a boundary member having a radially inner surface 322 that faces the centrifugal impeller 111. The radially inner surface 322 may be referred to as a compressor-facing surface or the impeller-facing surface.
As discussed above, centrifugal compressor 100 comprises a plurality of blades 112 mounted to a centrifugal impeller 111 that is coupled to a rotatable shaft 116. The space between the inner surface 322 of the shroud 320 and the blade tips 113 is referred to as the blade tip clearance 140 or clearance gap.
The shroud 320 is disposed between an inlet flowpath member 344 and an outlet flowpath member 345, which partially define a compressor inlet 346 and compressor outlet 347, respectively. In some embodiments, such as the embodiment illustrated in
Each of the disclosed components comprises a material having a coefficient of thermal expansion (CTE). The shroud 320 comprises a first material or combination of materials and has a first coefficient of thermal expansion (α1). In some embodiments, the shroud 320 may comprise Inconel, steel, or titanium.
In some embodiments, a thermal member 360 is coupled to the shroud 320 proximate the aft end 326. For example, in the illustrated embodiment a coupling member 327 extends axially forward from the aft end 326 to couple the thermal member 360 to the shroud 320. Thermal member 360 may be one or more hoops or rings, or may comprise more than one member or piece. In some embodiments, thermal member 360 may be integrally formed with the aft end 326, coupling member 327, or shroud 320.
The thermal member 360 comprises a second material or combination of materials and has a second coefficient of thermal expansion (α2). The thermal member 360 may comprise a low thermal expansion material. The thermal member 360 may comprise a material with lower thermal expansion than the shroud 320. In some embodiments, the thermal member 360 may comprise a nickel alloy, Inconel, titanium, or low-a steel. The second coefficient of thermal expansion may be less than the first coefficient of thermal expansion. In other words, the thermal member 360 may be configured to expand less, responsive to increasing temperatures, than the shroud 320.
The shroud 320 is coupled to a portion of the static engine casing 371 by a shroud arm 370. The shroud arm 370 may comprise a flexible portion 372. The flexible portion 372 may have a U-shaped cross section when viewed normal to the axis of rotation. The shroud arm 370 is coupled to the shroud 320 between the forward end 324 and aft end 326. The shroud arm 370 may be coupled to the shroud 320 at any point between the forward end 324 and aft end 326. In some embodiments the shroud arm 370 may be coupled to the shroud 320 at a midpoint between the forward end 324 and aft end 326, and/or may be coupled to the shroud 320 at the knee 328. Coupling the shroud arm 370 to shroud 320 at the knee 328 allows close control of the clearance gap 140 at the knee 328.
The shroud arm 370 divides the generally annular region that is radially outward and axially forward of the shroud 320 into a first cavity 380 and second cavity 382. The first cavity 380 is an inlet-side cavity and may be in fluid communication with the inlet 346. First cavity 380 may therefore be at a first pressure P1. The first cavity 380 may be at least partially bound by the shroud 320 and shroud arm 370.
The second cavity 382 is an outlet-side cavity and may be in fluid communication with the outlet 347. Second cavity 382 may therefore be at a second pressure P2. The second pressure P2 may be the discharge pressure of the centrifugal impeller 111. The second cavity 382 may be at least partially bound by the shroud 320 and shroud arm 370. In embodiments having a flexible portion 372 with a U-shaped cross section, an inner concave surface 383 of the U shape may be in fluid communication with the second cavity 382.
The differential pressure across the centrifugal compressor 100 may be proportional to the rotational speed of the centrifugal impeller 111. Therefore, the pressure difference between the first cavity 380 and the second cavity 382 may also be proportional to the rotational speed of the centrifugal impeller 111. Since a portion of the deflection experienced by the centrifugal impeller 111 during operation is due to mechanical and pressure loading, the differential pressure across the shroud arm 370 (i.e. between the first cavity 380 and the second cavity 382) may be proportional to that loading.
Although the shroud arm 370 is illustrated with a flexible portion 372 having a U-shaped cross section, the present disclosure is not so limited. The shape, thickness, radius, positioning, size, and connection points of the shroud arm 370 and flexible portion 372 may be altered to achieve a desired performance.
In some embodiments, one or more sensors 385 may be used to monitor the clearance gap 140. Such sensors 385 may be embedded in the shroud 320 for directly sensing the clearance gap 140, or may comprise various systems for indirectly sensing the clearance gap 140.
During operation, the shaft 116 is rotated at a high speed. Centrifugal impeller 111 and blades 112 are rotated with the shaft 116. Gas (e.g., air) is drawn from the inlet 346, through the rotating blades 112, and discharged at a higher pressure to the outlet 347. In some embodiments gas received at the inlet 346 of the centrifugal compressor 100 is the discharged gas of an axial compressor. The high speed rotation of the centrifugal impeller 111 and thermal heating of the centrifugal compressor 100 during operation cause the shape changes described above with reference to
The centrifugal impeller 111 comprises a third material or combination of materials and has a third coefficient of thermal expansion (α3). In some embodiments, the centrifugal impeller 111 may comprise a nickel alloy, titanium or titanium alloy, Inconel, Udimet, RR1000, or steel. In some embodiments the third coefficient of thermal expansion is the same or substantially the same as the second coefficient of thermal expansion. In some embodiments, the thermal member 360 expands responsive to increasing temperatures to a similar extent as the centrifugal impeller 111.
Responsive to the pressure and temperature changes caused by operation of the centrifugal compressor 100, the centrifugal impeller shroud assembly 300 is configured to alter the shape and/or position of the shroud 320 relative to the centrifugal compressor 100. Such changes in shape and/or position maintain the blade tip clearance 140 and resolve misalignment between the shroud 320 and centrifugal impeller 111 to ensure continued safe and efficient operation of the centrifugal compressor 100.
Increasing temperatures caused by operation of the centrifugal compressor 100 causes the shroud 320 to expand. The thermal member 360, having a lower thermal coefficient of expansion than the shroud 320, expands less than the shroud 320. The difference between the extent to which the shroud 320 and thermal member 360 expands results in deflection of the aft end 326. The deflection of the aft end 326 of shroud 320 caused by lesser expansion of the thermal member 360 is shown in
In some embodiments, the higher the temperatures experienced by the shroud 320 due to operation of the centrifugal compressor 100, the greater the degree of deflection of the aft end 326. Thermal member 360, shroud 320, and aft end 326 are subject to temperature changes based on exposure to the gasses flowing through the centrifugal compressor 100. Thermal member 360 and aft end 326 are exposed to gasses exiting the centrifugal compressor 100 at outlet 347, and are therefore heated to be generally at the operating temperatures of those gasses.
In some embodiments the thermal member 360 comprises a material that restricts thermal growth as compared to the material of the shroud 320. In some embodiments the thermal member 360 creates a moment about the aft end 326 of the shroud 320 by having a lower thermal growth than the shroud 320.
Expansion of the shroud 320 in the radial direction is illustrated by Arrow A1 in
The pressure differential across the centrifugal compressor 100 during operation results in a pressure differential between first cavity 380 and second cavity 382. This pressure differential causes flexion of the flexible portion 372, which in turn drives axial movement of the shroud 320. In
In embodiments having a flexible portion 372 with a U-shaped cross section, such as the embodiments illustrated in
Although the arrows of
The present disclosure therefore provides both thermally- and mechanically-driven mechanisms for passive control of the shape and positioning of the shroud 320. A thermal member 360, having a lower coefficient of thermal expansion than the shroud 320, expands less than the shroud when subject to operating temperatures and therefore causes deflection of the aft end 326. The thermal member 360 provides a thermally-driven mechanism for maintaining the clearance gap 140 during operation of the centrifugal compressor 100. A shroud arm 370 having a flexible portion 372 couples the shroud 320 to a static casing 371. The differential pressure across the shroud arm 370, caused by the differential pressure across an operating centrifugal compressor 100, results in axial movement or repositioning of the shroud 320. The shroud arm 370 provides a mechanically-driven mechanism for maintaining the clearance gap 140 during operation of the centrifugal compressor 100. In some embodiments, the thermally-driven mechanism—the thermal member 360—primarily maintains the clearance gap 140 and resolves misalignment during steady-state operating conditions, while the mechanically-driven mechanism—the shroud arm 370—primarily maintains the clearance gap 140 and resolves misalignment during transient operations.
The provision of both thermal and mechanical mechanisms for adjusting the shape and/or position of the shroud 320 is important because the deflection of the centrifugal impeller 111 as described with reference to
In addition to disclosing the systems described above, the present disclosure provides a method of dynamically changing the shape and/or position of a centrifugal compressor shroud 320.
Method 600 starts at Block 601. At Block 603, a thermal member 360 is mounted to a shroud 320 proximate the aft end 326. The thermal member 360 may be mounted to the shroud 320 via a coupling member 327. The thermal member 360 expands less than the shroud 320 responsive to increasing temperatures. The material of the thermal member 360 may be selected to thereby effect thermal deflection of the discharge end 326 of the boundary member in a manner similar to the thermal expansion of the discharge end 151 of the centrifugal impeller 111 during operation of the centrifugal impeller 111.
At Block 605, the shroud 320 is coupled to a static casing 371 by a shroud arm 370. The shroud arm 370 may comprise a flexible portion 372 that may have a U-shaped cross section. The shroud arm 370 may divide a first cavity 380 from a second cavity 382. The flexion of the flexible portion 372 of the shroud arm 370 may be selected to thereby effect axial movement of the knee portion 328 of the boundary member in a similar manner to the axial movement of the centrifugal impeller 111 responsive to changes in the differential pressure from the inlet end 115 to the discharge end 151 of the centrifugal impeller 111 during operation of the centrifugal impeller 111.
The centrifugal compressor 100 is then operated at Block 607, indicating that the rotatable centrifugal impeller is rotated. Operation of the centrifugal compressor 100 establishes a differential pressure across the centrifugal compressor 100 and increasing temperatures throughout the centrifugal compressor 100 and shroud 320, including proximate the aft end 326.
At Block 609 the thermal member 360 is expanded less than the shroud 320 responsive to the increasing temperatures, resulting in deflection of the shroud 320 proximate the aft end 326. The deflection may comprise a curling motion of the shroud 320 and/or aft end 326. In this step the discharge end 326 of the boundary member is deflected responsive to changes in the temperature of the fluid at the discharge end 326 by mounting a thermal member 360 to the shroud 320 proximate the discharge end 326 of the boundary member. The thermal member 360 comprises a material having a coefficient of thermal expansion (CTE) that is lower than the CTE of the shroud 320.
The flexible portion 372 is flexed at Block 611. Flexing the flexible portion 372 axially repositions the shroud 320. The flexible portion 372 flexes responsive to changes in differential pressure between first cavity 380 and second cavity 382. In this step the knee portion 328 of the boundary member is axially moved responsive to changes in the differential pressure between the fluid at the inlet end 324 and the fluid at the discharge end 326 of the boundary member by coupling the shroud 320 to a static casing 371 via a shroud arm 370. The shroud arm 370 has a flexible portion 372 configured to flex responsive to a differential pressure between the inlet end 324 and the discharge end 326 of the shroud 320.
The method may further comprise preventing further axial repositioning in an axially aft direction by engaging a receiving groove 329 of the shroud 320 with an outlet flowpath member 345. The method may further comprise sensing a clearance gap 140 between the shroud 320 and centrifugal compressor 100. The clearance gap 140 may be sensed with sensors 385. The method may further comprise deflecting the aft end 326 of the shroud 320 responsive to changes in the temperature of gasses exiting the centrifugal compressor 100 during operation. The method may further comprise axially repositioning the shroud 320 responsive to changes in differential pressure across the centrifugal compressor 100 during operation.
The method ends at Block 613.
The disclosed subject matter provides numerous advantages over the prior art. Notably, the disclosed systems and methods passively maintain the clearance gap and resolve misalignment between a rotatable centrifugal impeller and an impeller shroud. As discussed above, the change from an active clearance control system to a passive clearance control system greatly simplifies the design and operation of the centrifugal compressor, and removes the need for many complicated linkages and systems that contribute significant weight and/or require a significant amount of power to operate.
Maintaining an appropriately-sized clearance gap ensures safe and efficient operation of the centrifugal compressor, and the turbine engine as a whole. A dynamically moveable impeller shroud also improves operability of the centrifugal compressor by providing a wider range of efficient operating conditions. Minimizing the clearance gap provides increased centrifugal compressor performance and lower fuel consumption.
The disclosed subject matter of a thermal member and flexible shroud arm provides a system that is responsive to both thermal and mechanical changes in the operating environment. Further, the disclosed thermal member coupled proximate the aft end of the shroud approximates or closely matches the deflection experienced by a centrifugal impeller during operation. The disclosed systems and methods therefore allow for maintaining an appropriately-sized gap through the entire length of the shroud (i.e. from the forward end to the aft end), whereas the prior art typically requires monitoring and adjusting the clearance gap based only on a single or few points along the shroud. For example, in prior art systems that monitor and optimize the clearance gap at the knee, both excessive and/or insufficient clearance gaps may occur at the aft end of the shroud. In the disclosed systems and methods, the flexible shroud arm may be the primary driver to maintaining an effective clearance gap at the knee, while the thermal member may be the primary driver for maintaining an effective clearance gap at the aft end or exducer.
The disclosed systems and methods not only provide mechanisms for adjusting shroud shape and/or position based on thermal and mechanical loading of the centrifugal impeller, but allow those mechanisms to operate somewhat independently of each other. The temperature changes used as an input to adjust the aft end deflection of the shroud only minimally impacts the differential pressure across the shroud arm. Similarly, the differential pressure across the shroud arm that is used as an input to adjust the axial positioning of the shroud only minimally impacts the temperatures changes proximate the thermal member. The thermal and mechanical loading are therefore largely isolated from each other and the shroud is passively designed to respond to each at a different rate of speed and in a different manner.
Although the above description is directed to a centrifugal compressor, and more particularly to a centrifugal compressor in a gas turbine engine, the systems, methods, and principles disclosed herein are equally applicable to passive clearance control for a centrifugal impeller shroud in additional applications, such as a centrifugal pump.
Although examples are illustrated and described herein, embodiments are nevertheless not limited to the details shown, since various modifications and structural changes may be made therein by those of ordinary skill within the scope and range of equivalents of the claims.
| Number | Name | Date | Kind |
|---|---|---|---|
| 3085398 | Ingleson | Apr 1963 | A |
| 4069662 | Redinger et al. | Jan 1978 | A |
| 4247247 | Thebert | Jan 1981 | A |
| 4264271 | Libertini | Apr 1981 | A |
| 4472108 | Pask | Sep 1984 | A |
| 4683716 | Wright et al. | Aug 1987 | A |
| 4844688 | Clough et al. | Jul 1989 | A |
| 5017088 | Miraucourt et al. | May 1991 | A |
| 5018942 | Ciokajlo et al. | May 1991 | A |
| 5049033 | Corsmeier et al. | Sep 1991 | A |
| 5116199 | Ciokajlo | May 1992 | A |
| 5211534 | Catlow | May 1993 | A |
| 5263816 | Weimer | Nov 1993 | A |
| 5344284 | Delvaux et al. | Sep 1994 | A |
| 5427498 | Lehe et al. | Jun 1995 | A |
| 6273671 | Ress, Jr. | Aug 2001 | B1 |
| 6543992 | Webster | Apr 2003 | B2 |
| 6877952 | Wilson | Apr 2005 | B2 |
| 6935836 | Ress, Jr. et al. | Aug 2005 | B2 |
| 7079957 | Finnigan et al. | Jul 2006 | B2 |
| 7114914 | Gendraud et al. | Oct 2006 | B2 |
| 7165937 | Dong et al. | Jan 2007 | B2 |
| 7189057 | Lee | Mar 2007 | B2 |
| 7448849 | Webster et al. | Nov 2008 | B1 |
| 7575409 | Dierksmeier et al. | Aug 2009 | B2 |
| 7686569 | Paprotna et al. | Mar 2010 | B2 |
| 7688081 | Webster | Mar 2010 | B2 |
| 7824151 | Schwarz | Nov 2010 | B2 |
| 8047773 | Bruce et al. | Nov 2011 | B2 |
| 8087880 | Karafillis | Jan 2012 | B2 |
| 8105012 | Anema | Jan 2012 | B2 |
| 8210794 | Nolcheff | Jul 2012 | B2 |
| 8534996 | Pankey et al. | Sep 2013 | B1 |
| 8616827 | O'Leary | Dec 2013 | B2 |
| 8721270 | Graefe et al. | May 2014 | B2 |
| 8734090 | Lewis | May 2014 | B2 |
| 8790067 | McCaffrey et al. | Jul 2014 | B2 |
| 8894362 | Fretwell | Nov 2014 | B2 |
| 9121302 | Duong | Sep 2015 | B2 |
| 9435218 | Casavant et al. | Sep 2016 | B2 |
| 9441499 | Casavant et al. | Sep 2016 | B2 |
| 9587507 | Ottow | Mar 2017 | B2 |
| 9598971 | Hasnedl et al. | Mar 2017 | B2 |
| 9598975 | Uskert et al. | Mar 2017 | B2 |
| 9957830 | McCaffrey et al. | May 2018 | B2 |
| 10066497 | Duguay | Sep 2018 | B2 |
| 10113556 | Moniz et al. | Oct 2018 | B2 |
| 10227879 | Moniz et al. | Mar 2019 | B2 |
| 10309246 | Miranda | Jun 2019 | B2 |
| 10323535 | Davis et al. | Jun 2019 | B2 |
| 10329940 | Ballard et al. | Jun 2019 | B2 |
| 10358933 | Moxon | Jul 2019 | B2 |
| 20080069690 | Ivakitch | Mar 2008 | A1 |
| 20080134659 | Schwarz et al. | Jun 2008 | A1 |
| 20130202428 | Renard | Aug 2013 | A1 |
| 20160084101 | McCaffrey | Mar 2016 | A1 |
| 20160123172 | Mondal | May 2016 | A1 |
| 20170198709 | Moniz | Jul 2017 | A1 |
| 20170234147 | Moniz | Aug 2017 | A1 |
| 20180023412 | Rizzi et al. | Jan 2018 | A1 |
| 20180038380 | Morgan et al. | Feb 2018 | A1 |
| 20180112550 | Dierksmeier | Apr 2018 | A1 |
| Number | Date | Country |
|---|---|---|
| 02042197 | Feb 1990 | JP |
| 2014053722 | Apr 2014 | WO |
| Entry |
|---|
| European Search Report, dated Oct. 25, 2019, in EP Application No. 19177569.1. |
| Number | Date | Country | |
|---|---|---|---|
| 20190383304 A1 | Dec 2019 | US |
