Patent ID: 12215589

DESCRIPTION OF THE EMBODIMENTS

In the embodiment of the disclosure, a hole diameter of the through hole is larger than an outer diameter of the end portion of the inner shaft portion with the second thread portion, and the end portion of the inner shaft portion with the second thread portion is located in the through hole, so that the second thread portion is screwed with the first thread portion in the through hole.

In the embodiment of the disclosure, a region covered by the first convex portion structure in the axis direction overlaps with the through hole in the axis direction, and the end portion of the inner shaft portion with the second thread portion is provided within the region covered by the first convex portion structure in the axis direction.

In the embodiment of the disclosure, the gas turbine engine further includes: a housing, including the turbine wheel and the compressor wheel; and a separating wall, installed on the housing and separating the turbine wheel and the compressor wheel. A central hole portion is provided in a center of the separating wall. A hole diameter of the central hole portion is larger than an outer diameter of the thrust cancel disc. The thrust cancel disc is located in the central hole portion, so that an outer circumferential surface of the thrust cancel disc and an inner circumferential surface of the separating wall, that is, a wall surface of the central hole portion, are provided opposite to each other.

In the embodiment of the disclosure, a labyrinth seal structure is provided between the outer circumferential surface of the thrust cancel disc and the inner circumferential surface of the separating wall, that is, the wall surface of the central hole portion, for sealing.

In the embodiment of the disclosure, the driving member is a rotor of a motor generator.

FIG.1is a cross-sectional schematic view of the gas turbine engine cut along the axis direction when coupled with the driving member according to one embodiment of the disclosure.FIG.2is a partial schematic view of the turbine wheel, the compressor wheel, the rotary shaft, the thrust cancel disc, etc., used in the gas turbine engine shown inFIG.1, cut along the axis direction.FIG.3is a perspective schematic view of the turbine wheel, the compressor wheel, the rotary shaft, the thrust cancel disc, etc., used in the gas turbine engine shown inFIG.2, cut along the axis direction.FIG.4is an exploded schematic view of the turbine wheel, the compressor wheel, and the thrust cancel disc used in the gas turbine engine shown inFIG.2.FIG.5is a schematic view illustrating the thrust cancel disc used in the gas turbine engine shown inFIG.2in a state of canceling the thrust force acting between the turbine wheel and the compressor wheel.FIG.6is a partially enlarged schematic view of the gas turbine engine in area A shown inFIG.1.FIG.7is a partially enlarged schematic view of the gas turbine engine in area B shown inFIG.6. The specific structure and application of the gas turbine engine100in one embodiment of the disclosure are described below with reference toFIG.1toFIG.7. However, these are only some examples of the disclosure, and disclosure is not limited thereto.

Referring toFIG.1toFIG.4, in this embodiment, the gas turbine engine100includes a turbine wheel110, a compressor wheel120, a rotary shaft130, and a thrust cancel disc140. The compressor wheel120is coaxially configured with the turbine wheel110(e.g., both with axis centers that correspond to the axis direction L) and rotates integrally. The rotary shaft130includes an outer shaft portion132connected to the compressor wheel120, a penetration portion134extending along the axis direction L and formed at an axis center of the outer shaft portion132, and an inner shaft portion136passing through the penetration portion134and connected to the turbine wheel110, so that the rotation of the turbine wheel110is transmitted to a driving member. Furthermore, the thrust cancel disc140is provided between an inner surface S1of the turbine wheel110and an inner surface S2of the compressor wheel120. In this way, the rotation of the turbine wheel110may drive the compressor wheel120to rotate synchronously through the rotary shaft130and is transmitted to the driving member50through the rotary shaft130.

Specifically, in the embodiment shown inFIG.1, the gas turbine engine100further includes a diffuser150, a combustor160, and a turbine nozzle170. The turbine nozzle170surrounds the turbine wheel110, the combustor160surrounds the turbine nozzle170, and the diffuser150is provided between the compressor wheel120and the combustor160. In this way, the combustion air compressed by the compressor wheel120reaches the combustor160via the diffuser150, etc., and the combustion gas produced by mixing and combusting the fuel and the compressed combustion air enters the turbine nozzle170and expands in the turbine nozzle170, as a result, the turbine wheel110is able to start to rotate at a high speed and drives the compressor wheel120to rotate at a high speed through the rotary shaft130. In addition, the rotation of the turbine wheel110is transmitted to the driving member50through the rotary shaft130, and the combustion gas is discharged from the discharge portion O. However, the specific structure of the gas turbine engine100is not limited by the disclosure and may be adjusted according to needs.

In such a gas turbine engine100, as shown inFIG.1to3, the rotary shaft130is extended along the axis direction L, the outer shaft portion132is connected to the compressor wheel120, and the inner shaft portion136passing through the penetration portion134of the outer shaft portion132is connected to the turbine wheel110. As shown inFIG.2andFIG.3, the compressor wheel120has a hollow portion122extending along the axis direction L and formed at the axis center, and at least the inner shaft portion136of the rotary shaft130passes through the hollow portion122. For example, the end portion132aof the outer shaft portion132of the rotary shaft130is provided at the end of the hollow portion122of the compressor wheel120(and further penetrates the hollow portion122), and the inner shaft portion136extends further through the hollow portion122toward the inner surface S1of the turbine wheel110. Specifically, the end portion132aof the outer shaft portion132of the rotary shaft130is provided with splines on the outer circumference and engages with the splines provided on the inner circumference of the end of the hollow portion122of the compressor wheel120, thereby being coupled to each other via spline coupling. However, in other embodiments not shown, the end portion132aof the outer shaft portion132may also be provided at other locations of the compressor wheel120without penetrating the hollow portion122.

Furthermore, in this embodiment, as shown inFIG.2andFIG.3, the turbine wheel110has a first thread portion112protruding from the center of the inner surface S1of the turbine wheel110toward the inner surface S2of the compressor wheel120, and one end portion136aof the inner shaft portion136extends toward the inner surface S1of the turbine wheel110and has a second thread portion138screwed with the first thread portion112. It may be seen that at least the inner shaft portion136of the rotary shaft130passes through the hollow portion122of the compressor wheel120, and the rotary shaft130is screwed with the first thread portion112of the turbine wheel110protruding from the inner surface S1through the second thread portion138provided at the end portion136aof the inner shaft portion136, so that the turbine wheel110, the compressor wheel120, and the rotary shaft130are connected to each other. In this way, the compressor wheel120and the turbine wheel110may be coaxially configured through the rotary shaft130and may rotate integrally through the screwing of the first thread portion112and the second thread portion138.

In addition, in this embodiment, as shown inFIG.2toFIG.4, the thrust cancel disc140is configured in a disk shape, and a through hole142is provided in the center of the thrust cancel disc140, which is equivalent to a ring-shaped member. The thrust cancel disc140is connected to the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120, respectively. Furthermore, the two side surfaces of the thrust cancel disc140are respectively provided with an annular gear-shaped first convex portion structures144A and144B. Multiple teeth provided at the edges of the first convex portion structures144A and144B are continuously provided along the circumferential direction of the thrust cancel disc140and protrude toward the outside. Correspondingly, the inner surface S1of the turbine wheel110is provided with an annular gear-shaped second convex portion structure114(located on the outer circumferential side of the first thread portion112), and the inner surface S2of the compressor wheel120is provided with an annular gear-shaped second convex portion structure124(located on the outer circumferential side of the opening122aof the hollow portion122). The connection through the engagement of the annular gear-shaped first convex portion structures144A and144B and the annular gear-shaped second convex portion structures114and124is called curvic coupling. In this way, the thrust cancel disc140is connected to the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120, respectively, through coupling of the first convex portion structures144A and144B and the second convex portion structures114and124.

It may be seen that in this embodiment, the thrust cancel disc140is provided between the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120and is connected to the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120, respectively, through coupling (i.e., curvic coupling) of the first convex portion structures144A and144B and the second convex portion structures114and124. In this way, the compressor wheel120and the turbine wheel110may be tightly coupled through the thrust cancel disc140and rotate integrally. Moreover, the center of the through hole142of the thrust cancel disc140corresponds to the axis center of the turbine wheel110and the axis center of the compressor wheel120(e.g., both correspond to the axis direction L). In this way, the thrust cancel disc140may easily center the turbine wheel110and the compressor wheel120during assembly, especially reassembly. That is, the centers of the turbine wheel110, the thrust cancel disc140, and the compressor wheel120may be easily assembled in correspondence with the axis direction L. Accordingly, the gas turbine engine100may improve energy efficiency and improve assembly efficiency. However, the manner in which the thrust cancel disc140is coupled with the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120is not limited by the disclosure, which may be adjusted according to needs.

In addition, in this embodiment, as shown inFIG.5, during the rotation of the turbine wheel110and the compressor wheel120, the turbine wheel110bears the pressure P1from the outside to the inside and the pressure P2from the inside to the outside, thereby generating a thrust force F1toward the turbine wheel110. Similarly, the compressor wheel120bears the pressure P3from the outside to the inside and the pressure P4from the inside to the outside, thereby generating a thrust force F2toward the compressor wheel120. Under normal circumstances, the result of the thrust force F1toward the turbine wheel110and the thrust force F2toward the compressor wheel120constitutes a thrust force F3toward the rotary shaft130, thereby placing a burden on the bearing139(shown inFIG.1) that maintains the rotary shaft130rotatably on the driving member50. Correspondingly, in this embodiment, since the thrust cancel disc140is provided between the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120, the two opposite side surfaces of the thrust cancel disc140also generate corresponding thrust force F4and thrust force F5during the rotation. InFIG.5, although the two opposite side surfaces of the thrust cancel disc140are separated from the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120to show the pressure application state, in fact, the thrust cancel disc140is closely coupled with the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120through curvic coupling.

It may be seen that in this case, the thrust force F4generated by the thrust cancel disc140may be used to cancel at least part of the thrust force F1acting on the turbine wheel110, and the thrust force F5generated by the thrust cancel disc140may be used to cancel at least part of the thrust force F2acting on the compressor wheel120. In this way, even if the thrust force F1toward the turbine wheel110(canceled by the thrust force F4at least partially) and the thrust force F2toward the compressor wheel120(canceled by the thrust force F5at least partially) still constitutes the thrust force F3toward the rotary shaft130, the magnitude of the thrust force F3may be reduced (or the thrust force F3may be completely eliminate) through the thrust cancel disc140. In this way, the thrust cancel disc140may cancel the thrust forces F1and F2acting between the turbine wheel110and the compressor wheel120, thereby suppressing the burden on the bearing139used by the rotary shaft130and extending the life of the bearing139. In addition, the rotation of the turbine wheel110may be transmitted through the thrust cancel disc140and the compressor wheel120of considerable thickness coupled by curvic coupling. In this way, at least the inner shaft portion136of the rotary shaft130may be made thin, thereby reducing the weight of the rotary shaft130and the connected driving member50. However, the disclosure is not limited thereto and may be adjusted according to needs.

Furthermore, in this embodiment, as shown inFIGS.2and3, although the thrust cancel disc140is provided between the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120, since the through hole142is provided in the center of the thrust cancel disc140, the first thread portion112of the turbine wheel110or the end portion136aof the inner shaft portion136with the second thread portion138passes through the through hole142. In particular, the inner shaft portion136of the rotary shaft130passes through the hollow portion122of the compressor wheel120and extends outside the opening122a, so that the second thread portion138provided on the end portion136aof the inner shaft portion136is screwed with the first thread portion112on the outside of the hollow portion122. At this time, although the inner surface S1of the turbine wheel110and the inner surface S2of the compressor wheel120are respectively located on the opposite sides of the thrust cancel disc140, by providing the through hole142in the center of the thrust cancel disc140, at least one of the first thread portion112and the second thread portion138may pass through the through hole142for screwing. It may be seen from this that the configuration of the thrust cancel disc140does not interfere with the screwing of the second thread portion138of the rotary shaft130and the first thread portion112of the turbine wheel110. Moreover, since an additional output shaft is not required by the turbine wheel110for penetrating the hollow portion122of the compressor wheel120as in conventional technology, it is not necessary to screw the first thread portion112and the second thread portion138at a location such as the hollow portion122where it is difficult to confirm the screwing condition. That is, the first thread portion112of the turbine wheel110and the second thread portion138of the rotary shaft130are screwed together around the thrust cancel disc140, that is, in the space between the turbine wheel110and the compressor wheel120, thereby allowing easy confirmation on the screwing condition. Accordingly, the gas turbine engine100may improve energy efficiency and improve assembly efficiency.

Furthermore, as an example, as shown inFIG.2andFIG.3, the hole diameter of the through hole142of the thrust cancel disc140is larger than the outer diameter of the end portion136aof the inner shaft portion136with the second thread portion138, and the end portion136aof the inner shaft portion136with the second thread portion138is located in the through hole142, so that the second thread portion138screws with the first thread portion112in the through hole142. That is, the first thread portion112of the turbine wheel110and the second thread portion138of the rotary shaft130both penetrate into the through hole142to be screwed together. Furthermore, the region R (as shown inFIG.2) covered by the first convex portion structures144A and144B on two side surfaces of the thrust cancel disc140in the axis direction L overlaps with the through hole142in the axis direction L. That is, the positions of the first convex portion structures144A and144B of the thrust cancel disc140in the axis direction L are further outside than the position of the through hole142in the axis direction L. Furthermore, the end portion136aof the inner shaft portion136with the second thread portion138is provided in the region R covered by the first convex portion structures144A and144B in the axis direction L. In this way, the end portion136aof the inner shaft portion136is configured within the region R covered by the first convex portion structures144A and144B in the axis direction L, enabling the second thread portion138provided on the end portion136aof the inner shaft portion136to be screwed to the first thread portion112in the through hole142.

However, in other embodiments not shown, the first thread portion112of the turbine wheel110may pass through the through hole142and screw with the second thread portion138near the inner surface S2of the compressor wheel120(i.e., to the left side of the through hole142); alternatively, the end portion136aof the inner shaft portion136with the second thread portion138may pass through the through hole142and screw with the first thread portion112near the inner surface S1of the turbine wheel110(i.e., to the right side of the through hole142); alternatively, during the assembly process, the first thread portion112and the second thread portion138may be screwed to each other on one side of the through hole142, and then the first thread portion112and the second thread portion138may be located in the through hole142by moving the rotary shaft130, as long as the center of the thrust cancel disc140is provided with the through hole142, and the first thread portion112of the turbine wheel110or the end portion136aof the inner shaft portion136with the second thread portion138passes through the through hole142for screwing. The disclosure does not limit the screwing locations of the first thread portion112and the second thread portion138or the relative positions with the thrust cancel disc140. Moreover, although the first thread portion112of the turbine wheel110is a male thread portion and the second thread portion138of the rotary shaft130is a female thread portion, the disclosure is not limited thereto and may be adjusted according to needs.

In addition, in this embodiment, as shown inFIG.1, the gas turbine engine100further includes a housing180. The housing180includes the turbine wheel110and the compressor wheel120, and further includes the rotary shaft130, the thrust cancel disc140, the diffuser150, the combustor160, the turbine nozzle170, etc., as mentioned above. In this way, the gas turbine engine100may be easily connected to the driving member50as one assembly; for example, another end portion132bof the outer shaft portion132of the rotary shaft130opposite to the end portion132apenetrates from the housing180and is coupled to the driving member50. The driving member50is, for example, a rotor of the motor generator20, and there are structures such as a stator22and an outer casing24of the motor generator20provided outside. The rotary shaft130of the gas turbine engine100is rotatably provided on the outer casing24of the motor generator20through the bearing139and is connected to the driving member50serving as the rotor of the motor generator20. In this way, the rotation of the turbine wheel110of the gas turbine engine100may be transmitted to the driving member50through the rotary shaft130for rotational driving. However, in other embodiments not shown, the driving member50may also be a rotating fan of a jet engine, a transmission mechanism for vehicle, etc., the disclosure is not limited thereto and may be adjusted according to needs.

Furthermore, in this embodiment, as shown inFIG.1, the gas turbine engine100further includes a separating wall190. The separating wall190is installed on the housing180(e.g., inside the housing180) and separates the turbine wheel110and the compressor wheel120. As shown inFIG.1,FIG.6, andFIG.7, a central hole portion192is provided in the center of the separating wall190. The hole diameter of the central hole portion192is larger than the outer diameter of the thrust cancel disc140, and the thrust cancel disc140is located in the central hole portion192. It may be seen from this that the separating wall190is formed into an annular structure and surrounds the outer circumference of the thrust cancel disc140to separate the turbine wheel110and the compressor wheel120, so that the thrust cancel disc140is located in the central hole portion192of the separating wall190, and an outer circumferential surface140aof the thrust cancel disc140and an inner circumferential surface190aof the separating wall190, that is, a wall surface192aof the central hole portion192, are provided opposite to each other. As shown inFIG.6andFIG.7, a labyrinth seal structure70is provided between the outer circumferential surface140aof the thrust cancel disc140and the inner circumferential surface190aof the separating wall190, that is, the wall surface192aof the central hole portion192(as shown in area B inFIG.1), for sealing.

Specifically, in this embodiment, as shown inFIG.6andFIG.7, the labyrinth seal structure70includes a first sealing portion72formed on the outer circumferential surface140aof the thrust cancel disc140. The first sealing portion72is provided with a first concave and convex structure72a. Correspondingly, the inner circumferential surface190aof the separating wall190, that is, the wall surface192aof the central hole portion192, is a plane facing the first concave and convex structure72ain a cross-sectional view and located on the outer circumferential side of the first sealing portion72. In this way, the first sealing portion72with the first concave and convex structure72aforms a labyrinth flowing path space between the outer circumferential surface140aof the thrust cancel disc140and the inner circumferential surface190aof the separating wall190. In this way, the labyrinth seal structure70may narrow the flowing path space through the first concave and convex structure72a, so that the fluid generates pressure resistance and becomes difficult to flow. Thus, the area between the outer circumferential surface140aof the thrust cancel disc140and the inner circumferential surface190aof the separating wall190, that is, the wall surface192aof the central hole portion192, is sealed.

Furthermore, in this embodiment, the first sealing portion72is a sealing structure integrally formed on the outer circumferential surface140aof the thrust cancel disc140, however, in other embodiments not shown, it may also be an additional sealing member provided on the outer circumferential surface140aof the thrust cancel disc140. Similarly, the labyrinth seal structure70may also include a second sealing portion with a second concave and convex structure, which is formed or provided on the inner circumferential surface190aof the separating wall190, that is, the wall surface192aof the central hole portion192, so as to replace or be combined with the first sealing portion72. Moreover, in other embodiments not shown, a contact sealing structure may also be used to seal the area between the outer circumferential surface140aof the thrust cancel disc140and the inner circumferential surface190aof the separating wall190, that is, the wall surface192aof the central hole portion192, or there may be no sealing structure. The disclosure is not limited thereto and may be adjusted according to needs.

To sum up, in the gas turbine engine of the disclosure, the thrust cancel disc is provided between the inner surface of the turbine wheel and the inner surface of the compressor wheel and is connected to the inner surface of the turbine wheel and the inner surface of the compressor wheel, respectively, through coupling (e.g., curvic coupling) of the annular gear-shaped first convex portion structures provided on the two side surfaces thereof and the annular gear-shaped second convex portion structures provided on the inner surface of the turbine wheel and the inner surface of the compressor wheel, respectively. Furthermore, the turbine wheel has a first thread portion protruding from the inner surface, at least the inner shaft portion of the rotary shaft passes through the hollow portion of the compressor wheel, and one end portion of the inner shaft portion has a second thread portion. The through hole is provided in the center of the thrust cancel disc, and the first thread portion of the turbine wheel or the end portion of the inner shaft portion with the second thread portion passes through the through hole. The end portion of the inner shaft portion with the second thread portion is located in the through hole, so that the second thread portion is screwed with the first thread portion in the through hole. In this way, the thrust cancel disc may cancel the thrust force acting between the turbine wheel and the compressor wheel, thereby suppressing the burden on the bearing that maintains the rotary shaft rotatably. In addition, since the rotation of the turbine wheel is transmitted to the compressor wheel through the thrust cancel disc by curvic coupling, the output shaft of the turbine wheel in conventional technology is not required, and the energy efficiency may be improved or the material cost may be lowered by the reduced weight including the rotation mass of the turbine wheel. Furthermore, the thrust cancel disc may also easily center the turbine wheel and the compressor wheel during assembly, especially reassembly. Moreover, the first thread portion of the turbine wheel and the second thread portion of the rotary shaft are screwed together around the thrust cancel disc, that is, in the space between the turbine wheel and the compressor wheel, thereby allowing easy confirmation on the screwing condition. Accordingly, the gas turbine engine of the disclosure may improve energy efficiency and improve assembly efficiency.

Finally, it should be noted that the foregoing embodiments are only used to illustrate the technical solutions of the disclosure, but not to limit the disclosure; although the disclosure has been described in detail with reference to the foregoing embodiments, persons of ordinary skill in the art should understand that the technical solutions described in the foregoing embodiments can still be modified, or parts or all of the technical features thereof can be equivalently replaced; however, these modifications or substitutions do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the disclosure.