阅读说明：本技术 用于质谱仪的涡轮分子泵 (Turbo-molecular pump for mass spectrometer ) 是由 约亨·弗兰岑 乌尔斯·斯坦纳 于 2019-08-14 设计创作，主要内容包括：本发明涉及能够实现高泵速的涡轮分子泵。本发明提出使用一个或多个笼状转子级来优化具有低气流和低极限压力的真空系统上的泵速。这允许较小的电动机以及较小的整体形状因子,并且特别适用于紧凑型质谱仪和台式质谱仪。(The present invention relates to a turbomolecular pump capable of realizing a high pumping speed. The present invention proposes the use of one or more caged rotor stages to optimize pump speed on vacuum systems with low gas flow and low ultimate pressure. This allows for smaller motors and smaller overall form factors, and is particularly suitable for compact mass spectrometers and bench top mass spectrometers.)

1. A turbomolecular pump comprising a fixed frame structure and at least one rotor stage at a low pressure input region, wherein a rotor in the at least one rotor stage rotates relative to the fixed frame structure during operation, and the rotor has a central shaft receiving member from which a first rotor blade section extends substantially radially outward and is connected to a second rotor blade section which extends substantially coaxially with and along the central shaft receiving member towards a high pressure output region, the first and second rotor blade sections deflecting gaseous matter substantially in a near axial and radially inward direction during operation.

2. The turbomolecular pump of claim 1, wherein the rotor blades in the first rotor blade section are inclined with respect to a first plane perpendicular to the central shaft receiving member, and the rotor blades in the second rotor blade section are inclined with respect to an envelope profile of the substantially hollow cylindrical shape generated by the second rotor blade section.

3. The turbomolecular pump of claim 1, further comprising a third rotor blade section extending substantially radially outward from the central shaft receiving member and connected to the second rotor blade section at a location between the low pressure input region and the high pressure output region to enhance mechanical stability, wherein during operation, the third rotor blade section deflects gaseous matter substantially in a near-axial direction.

4. The turbomolecular pump of claim 3, wherein the rotor blades in the third rotor blade section are inclined with respect to a second plane perpendicular to the central shaft receiving member.

5. The turbomolecular pump of claim 1, wherein the number of rotor blades in at least one of the first, second and third rotor blade parts is odd to reduce resonant vibrations.

6. The turbomolecular pump of claim 1, wherein adjacent rotor blades in at least one of the first, second and third rotor blade sections substantially overlap each other to prevent gaseous matter that has entered inside from escaping or otherwise exiting in a direction other than towards the high pressure output region.

7. The turbomolecular pump of claim 1, further comprising an annular support structure connected with a distal end of a rotor blade in the second rotor blade section to enhance mechanical stability.

8. The turbomolecular pump of claim 1, wherein a rotor blade in the second rotor blade section comprises a rounded edge at a connection point with a rotor blade in the first rotor blade section.

9. The turbomolecular pump of claim 1, wherein the first rotor blade section transitions into the second rotor blade section.

10. The turbomolecular pump of claim 1, wherein the proximal axial extension of the second rotor blade section is equal to or greater than the radial extension of the first rotor blade section.

11. The turbomolecular pump of claim 1, wherein the central shaft receiving member comprises a hollow receptacle for accommodating a drive shaft, which can rotate the central shaft receiving member.

12. The turbomolecular pump of claim 1, wherein the central shaft receiving member flares, at least in a partial section, from the high pressure output region to the low pressure input region to impart additional momentum in a direction towards the high pressure output region to the gaseous matter deflected from the second rotor blade portions in a generally radially inward direction.

13. The turbomolecular pump of claim 1, wherein rotor blades in the second rotor blade section are helically twisted along the substantially hollow cylindrical envelope profile generated by the second rotor blade section to deflect the gaseous substance from the second rotor blade section substantially in a proximal-axial and radially-inward direction.

14. A turbomolecular pump according to claim 1, wherein the rotor in the at least one rotor stage is made of a stable metal such as aluminium, magnesium, titanium or an alloy of said stable metals.

15. The turbomolecular pump of claim 1, wherein in a multiport configuration, the turbomolecular pump further comprises a second rotor stage located at a position spaced apart from the low pressure input region, the second rotor stage having a similar configuration to the at least one rotor stage located at the low pressure input region.

16. A mass spectrometer, comprising:

-a receiver having at least two adjacent compartments maintained at a pressure substantially below ambient atmospheric pressure during operation; and

-the multi-port configured turbomolecular pump of claim 15, mounted at the at least two adjacent compartments, such that the second rotor blade section substantially protrudes into a first of the at least two adjacent compartments, and the second rotor stage is fluidly connected with a second of the at least two adjacent compartments.

17. A mass spectrometer, comprising:

-a receiver having at least one compartment, the at least one compartment being maintained at a pressure substantially below ambient atmospheric pressure during operation; and

-a turbomolecular pump according to claim 1, mounted at the at least one compartment such that the second rotor blade sections substantially protrude into the at least one compartment.

18. The mass spectrometer of claim 17, wherein the at least one compartment contains at least one mass analyzer or at least one gas source, and the second rotor blade section protrudes directly exposed to gaseous species escaping or otherwise exiting the at least one mass analyzer and emanating from the at least one gas source, respectively.

19. The mass spectrometer of claim 17, wherein the at least one compartment comprises at least one of a time-of-flight drift tube, a golden den type mass analyzer, a 2D or 3D ion trap, a mass filter, and an ion cyclotron resonance cell.

Technical Field

The present invention relates to a turbomolecular pump capable of realizing a high pumping speed. The present invention proposes to optionally use one or more novel caged rotor stages (rotor stages) in addition to the conventional rotor stages commonly used in the art to optimize the pump speed of a vacuum system with low gas flow and low ultimate pressure. This allows for smaller motors and smaller overall form factors, and is particularly suitable for compact Mass Spectrometers (MS) and bench top mass spectrometers.

Background

Conventional turbomolecular pumps typically consist of a low pressure input stage and a high pressure exhaust section. The low-voltage input stage consists of a stack of rotors, each having a plurality of angled vanes, mounted in a tubular housing, rotating at very high tangential speeds. Gas molecules that are impacted by the underside of the angled vanes move with momentum in the direction of the high pressure exhaust section.

The low-voltage input stage therefore consists of a stacked disk-shaped turbine rotor with radially extending rotor blades. Typically, there is a non-rotating stator with opposing angled radial vanes between each rotor. The pump speed of a turbomolecular pump is given by the blade diameter and the rotational speed (revolutions per minute, RPM) of the turbine rotor blades. The rotational speed is limited by the strength of the blade material, which must withstand centrifugal forces and be heated to a temperature resulting from the total gas load to be pumped.

Experience has shown that the material strength of the vanes of currently commercially available turbomolecular pumps has been optimized and cannot be improved significantly. In many cases, for example in mass spectrometers, the gas load is minimal. In such analyzers with long ion trajectories, the ion mean free path (mean propagation distance between two collisions with other gaseous species) should be kept as long as possible, which means that the absolute end pressure (end pressure) must be as low as possible. To obtain a mean free path of more than 10 cm, less than 10 is required^-5Torr (-1.3X 10)^-3Pascal) pressure. In many high resolution MS systems (e.g., time-of-flight, ion cyclotron resonance cell) and from Thermo Fisher Scientific

(orbitrap)), ions can stay in the analyzer for seconds, which requires a mean free path of more than one meter. In this system, less than 10 is required^-7Torr (-1.3X 10)^-5Pascal) pressure, e.g. up to 10^-11Torr (-1.3X 10)^-9Pascal).

To achieve this low end pressure in the presence of gas loading, the pump speed needs to be high, which currently requires larger pump sizes with larger rotor diameters. This in turn requires a larger vacuum chamber, which in turn increases the overall system size and greatly increases cost. The gas load of the MS system comes primarily from the ion source and some surface outgassing. In some cases, additional gas is introduced into the collision cell of the MS system to cool the ions or fragment the molecular ions, the gas eventually leaking and thus increasing the gas load of other parts of the vacuum receiver of the mass spectrometer.

In many cases, mass spectrometers include an inlet and an ion source with a high gas load. If these regions can operate at higher pressures, a multi-port turbo-molecular pump can be used. In this case, the interstage opening is placed at the appropriate pressure level of the pump. The height and width of these openings are selected to support sufficient airflow. To optimize the gas flow, the rotor and stator may be removed in these sections.

Turbomolecular pumps also typically contain so-called Holweck stages, which are of the type with a drag compression stage (drag compression stage) having a radial flow component. In essence, the Holweck stage is a rotating helical rotor that rotates in a stationary cylinder. This creates a rotating channel towards the higher pressure region. Surface friction is used to move molecules along the channel. Another method of drag stage involves rotating a disk with or without grooves in the disk (so-called Gator stage). This will generate a radial flow component. However, all of these known drag stages are located close to the high pressure exhaust section, rather than at the low pressure end of the volume to be evacuated.

Disclosure of Invention

The invention relates to a turbomolecular pump comprising a fixed (static) frame structure and at least one rotor stage at the low-pressure inlet region, wherein the rotor in at least one rotor stage rotates relative to the stationary frame structure during operation, and the rotor has a central shaft receiving member, which may comprise a hollow receptacle for receiving a drive shaft, which is capable of rotating the central shaft receiving member, the first rotor blade section extending generally radially outwardly from the central shaft receiving member and being connected to the second rotor blade section, for example (smoothly) into a second rotor blade section, which extends substantially coaxially (and along) the central shaft receiving member towards the high pressure output region, wherein during operation, the first and second rotor blade sections deflect gaseous matter generally in an axially and radially inward direction.

The basic idea of the invention is to supplement the conventional only radially extending rotor blades in the first rotor stage at the low pressure input region with a cage having a set of additional near-axis rotor blade sections (sub blade sections) connected to, preferably integrally connected to, a known top radial rotor blade section. In this design, the rotor blade portions cover the outer perimeter and top of an abstract rotor "cage". By arranging the proximal rotor blade portion of such a turbomolecular pump to be at least partially (and preferably fully) fluidly exposed to the volume to be evacuated, the pump speed can be significantly increased, since the pump speed is proportional to both the blade speed and the rotor blade portion length along the axis of rotation. In addition, this makes it possible to extract the gaseous substances also perpendicularly to the rotor axis (drive shaft axis) and in principle along the entire circumference of 360 degrees around the pump rotor stage, which correspondingly increases the effective pumping cross-sectional area. This means that the pump can be reduced in size compared to conventional designs without any loss of pumping power at the same time.

In various embodiments, the rotor blades in the first rotor blade section may be inclined with respect to a first plane perpendicular to the central shaft receiving member, and the rotor blades in the second rotor blade section may be inclined with respect to a generally hollow cylindrical envelope profile generated by the second rotor blade section, which may further include rounded edges (rounded edges) at the points of connection with the rotor blades in the first rotor blade section.

In various embodiments, a third rotor blade section may be foreseen that extends generally radially outward from the central shaft receiving member and is connected to the second rotor blade section at a location between the low pressure input region and the high pressure output region to enhance the mechanical stability of the second rotor blade section, wherein the third rotor blade section deflects gaseous matter generally in the proximal axial direction during operation. Preferably, the rotor blades in the third rotor blade section are inclined with respect to a second plane perpendicular to the central shaft receiving member.

In various embodiments, the number of rotor blades in at least one of the first and second rotor blade sections (which may be the first, second and/or third rotor blade sections, as the case may be) may be odd to reduce resonant vibrations that may occur due to unavoidable mechanical tolerances in the production process.

In various embodiments, adjacent ones of the first and second rotor blade sections (which may be the first, second and/or third rotor blade sections, as the case may be) generally overlap one another to prevent gaseous matter that has entered the interior from escaping or otherwise exiting in directions other than toward the high pressure output region.

In various embodiments, an annular support structure may be foreseen, which is connected with the distal end of the rotor blade in the second rotor blade section to enhance mechanical stability.

In various embodiments, the proximal axial extension (para extension) of the second rotor blade portion may be equal to or greater than the radial extension of the first rotor blade portion. Depending on the amount of proximal axial extension (or height) of the caged rotor, the pump speed can be increased by a factor of three or more compared to a conventional turbomolecular pump of the same diameter having only a proximal pumping action.

In various embodiments, the central shaft receiving member may flare (flare) in at least a partial section from the high pressure output region to the low pressure input region to impart additional momentum in a direction toward the high pressure output region to gaseous matter deflected in a generally radially inward direction from the second rotor blade portion.

In various embodiments, the rotor blades in the second rotor blade section may be helically twisted along the generally hollow cylindrical envelope profile generated by the second rotor blade section to deflect gaseous matter from the second rotor blade section generally in a proximal-to-axial and radially-inward direction.

In various embodiments, at least one conventional rotor-stator stage having radially extending interdigitated rotor-stator vanes may be located downstream of the at least one rotor stage at the low pressure input region. Furthermore, conventional rotor-stator stages may include, for example, Holweck and/or Gator stages, as deemed appropriate by those skilled in the art.

In various embodiments, the rotors in at least one rotor stage may be made of a stable metal such as aluminum, magnesium, titanium, or alloys thereof (e.g., gamma titanium aluminum). Preferably, the rotors in at least one rotor stage are made by additive manufacturing, for example by fusing or casting in one piece using metal powder.

In various embodiments, the fixed frame structure may include a plurality of arcs that converge at a low pressure input region of the central shaft receiving member in the bearing. Preferably, the bearing is one of a magnetic bearing (e.g. having a plurality of permanent magnets) and a ball bearing (e.g. comprising a plurality of ceramic balls having an ultra-smooth surface). It is also preferred that the fixed frame structure further comprises a flange spaced from the low pressure input region along the central axis receiving member, the plurality of arcs being connected to the flange.

In some embodiments, the first rotor blade portion adjacent the low pressure input region may be comprised of a substantially gas impermeable member, such as a substantially solid flat plate or disk, such that the first rotor blade portion exerts little, if any, proximal pumping action. The majority of the pumping action is then effected by the circumferentially radially inward pumping movement of the proximal rotor blade portion. It goes without saying that such a configuration presents the greatest potential when the proximal rotor blade portion is fully exposed to the volume to be evacuated and when the central shaft receiving member is provided with an angled surface, such as a frustoconical diverging surface, and which deflects the gaseous species propelled radially inwardly under the effect of the rotation of the proximal rotor blade portion in the proximal axial direction towards the high pressure output region of the turbomolecular pump.

The invention also relates to a mass spectrometer comprising: receiver having at least one compartment which is maintained at a pressure substantially below ambient atmospheric pressure during operation, for example below 10^-5Torr (-1.3X 10)^-3Pascal) less than 10^-7Torr (-1.3X 10)^-5Pascal) or even below 10^-11Torr (-1.3X 10)^-9Pascal); and a turbomolecular pump according to any of the above embodiments, mounted at the at least one compartment such that the second rotor blade sections substantially protrude into the at least one compartment, thereby extracting gaseous substances from the at least one compartment in a radially inward direction in addition to only in a proximal axial direction as in conventional turbomolecular pumps.

In various embodiments, the at least one compartment may contain at least one mass analyzer or at least one gas source (e.g., a wall degas, collision cell, or gas operated ion source), and the second rotor blade portion may protrude to be directly exposed to gaseous species escaping or otherwise exiting the at least one mass analyzer and emanating from the at least one gas source, respectively. Preferably, at least one compartment contains a time-of-flight drift tube (time-of-flight drift tube), a Kingdon type mass analyser (e.g. from Thermo Fisher Scientific)

) At least one of a 2D or 3D ion trap, a mass filter and an ion cyclotron resonance cell.

In various embodiments, coinciding with the multiport configuration, a second rotor stage is foreseen, located at a position spaced from the low pressure input area, having a similar configuration (cage) to at least one rotor stage located at the low pressure input area. It goes without saying that any features and characteristics explained with reference to at least one rotor stage at the low-pressure input region as above apply equally to this second rotor stage, which serves to evacuate the individual compartments to a slightly higher pressure level than the rotor stage at the low-pressure input region. It is particularly preferred that any rotor blade portion extending proximally in the second rotor stage has a smaller proximal axial extension than in the first rotor stage at the low pressure input region (i.e., the second rotor stage may be flatter) in order to mitigate the additional aerodynamic strain created by the higher pressure level at the intermediate pumping port. It goes without saying that in a further development of the technical teaching, a turbomolecular pump may have more than two rotor stages of novel design (in addition to the conventional rotor-stator stages) with respective port openings for fluid connection with other compartments to be evacuated to slightly different pressure levels.

The invention also relates to a mass spectrometer comprising: a receiver having at least two adjacent compartments that are maintained at (different) pressures substantially below ambient atmospheric pressure during operation; and a multi-port configured turbomolecular pump according to any of the embodiments described above, mounted at least two adjacent compartments, such that the second rotor blade section (the second rotor blade section of the first rotor stage located at the low pressure input region) substantially protrudes into a first compartment (maintained at a lowest pressure level) of the at least two adjacent compartments, and the second rotor stage is fluidly connected with a second compartment (maintained at a higher pressure level relative to the first compartment) of the at least two adjacent compartments.

Drawings

The invention may be better understood by reference to the following drawings. The components in the figures are not necessarily to scale, emphasis instead being placed upon illustrating the principles of the invention (generally, schematically):

fig. 1 schematically depicts a principle based on the present invention.

FIG. 2 presents several views of a first novel rotor design in accordance with the principles of the present invention.

FIG. 3 presents several views of another new rotor design in which the first radial rotor blade portion at the low pressure input end smoothly transitions to the proximal rotor blade portion.

FIG. 4A shows several views of yet another novel rotor design in which the rotor blades in the near-axis rotor blade section are helically deformed along a circumferential profile.

For clarity, fig. 4B complements the illustration in fig. 4A with less detail.

Fig. 5A shows a turbomolecular pump including a novel rotor design and its exemplary implementation in a receiver of a mass spectrometer.

Fig. 5B illustrates another exemplary embodiment of a turbomolecular pump featuring a novel rotor design in the drift tube of a time-of-flight mass analyzer.

Fig. 6A depicts a multi-port turbomolecular pump that includes a novel rotor design in several different views.

Fig. 6B depicts an exemplary embodiment of a multiport turbomolecular pump as shown in fig. 6A in a receiver of a mass spectrometer.

Detailed Description

While the invention has been shown and described with reference to a number of different embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the scope of the invention as defined by the appended claims.

The basic idea of the invention is to increase the pump speed by increasing the rotor blade cross section exposed to the chamber to be evacuated. This increases the likelihood that molecules will impact the rotor blade under high to ultra-high vacuum. With reference to the concept schematically illustrated in fig. 1, this object may be achieved by providing a rotor blade assembly of cage-like construction, which is preferably completely exposed to the vacuum chamber. The caged rotor blade assembly includes rotor blade portions arranged proximally along a circumference of an imaginary "cage". Additionally, the caged rotor blade assembly may include one or more sets of radial rotor blade portions to hold the proximal rotor blade portions in place.

The pump speed is increased by the length of the part of the near-axis rotor blade moving at the peripheral speed compared to the tip only (active) of the radially extending rotor blade in conventional turbomolecular pumps known in the prior art. This exposed arrangement also allows molecules to impact and be drawn into the caged rotor assembly radially inward from all sides and proximally, see the lower view in fig. 1. This is particularly important at pressures with mean free path greater than 10 cm. By virtue of the vacuum pressure achieved at the low pressure input region and the near axial extension of the near axial rotor blade portion, the pump speed can be significantly increased compared to a conventional turbomolecular pump of the same diameter.

Fig. 2 shows a first example of a novel cage rotor design in several views. Left side of the first row: a bottom plan view supplemented by a side cross-sectional view on the right and an isometric cross-sectional view further to the right; left side of second row: a plan side view supplemented by a cutaway plan top view on the right and an isometric view further to the right; third row left: a plan top view.

In the illustrated embodiment, the rotor 200 has a central shaft receiving member 202, and at the low pressure input region 204A, a first rotor blade portion 206A extends generally radially outward from the central shaft receiving member 202 and is connected with a second rotor blade portion 206B, the second rotor blade portion 206B extending generally coaxially with the central shaft receiving member 202 and along the central shaft receiving member 202 toward the high pressure output region 204B. During operation, the first and second rotor blade sections 206A and 206B deflect gaseous matter generally in a proximal axial and radially inward direction. In this example, the proximal axial extension X of the second rotor blade portion 206B is greater than the radial extension R of the first rotor blade portion 206A. The rotor blades in the second rotor blade portion 206B include a rounded edge 212 at the end toward the low pressure input region 204A.

The rotor blades in the first rotor blade section 206A are inclined with respect to a first plane P1 perpendicular to the central shaft receiving member 202, and the rotor blades in the second rotor blade section 206B are inclined with respect to a generally hollow cylindrical envelope profile C1 generated by the second rotor blade section 206B.

Third rotor blade portion 206C extends generally radially outward from central shaft receiving member 202 and is connected to second rotor blade portion 206B at a location between low pressure input region 204A and high pressure output region 204B for enhanced mechanical stability. During operation, the third rotor blade section 206C deflects gaseous matter generally in the proximal axial direction. The rotor blades in third rotor blade portion 206C are canted relative to a second plane P2 perpendicular to central shaft receiving member 202 so as to impart additional paraxial momentum toward high pressure output region 204B to gaseous matter captured into caged rotor 200 during rotation.

Adjacent ones of the first, second and third rotor blade portions 206A, 206B, 206C generally overlap one another such that there is little to no direct line of sight (direct line of sight) from the interior to the exterior, so as to prevent gaseous matter that has entered the interior from escaping or otherwise exiting in directions other than toward the high pressure output region 204B.

An annular support structure 208 is coupled to the distal end of the rotor blade in second rotor blade section 206B to enhance mechanical stability.

The central shaft receiving member 202 includes a hollow receiver 214 for receiving a drive shaft (not shown) that enables rotation of the central shaft receiving member 202. The central shaft receiving member 202 also includes thickened sections 210A and 210B, the thickened sections 210A and 210B being associated with (corresponding ones) of the first and third rotor blade portions 206A and 206C, respectively, the first and third rotor blade portions 206A and 206C having rotor blades extending generally radially, the thickened sections 210A and 210B flaring (frustoconical) from the high pressure output region 204B to the low pressure input region 204A to impart additional momentum in a direction toward the high pressure output region 204B to gaseous matter deflected from the second rotor blade portion 206B in a generally radially inward direction.

Fig. 3 shows another example of the novel cage rotor design in several views. Left side of the first row: a bottom plan view supplemented by a side cross-sectional view on the right and an isometric cross-sectional view further to the right; left side of second row: a plan side view supplemented by a cutaway plan top view on the right and an isometric view further to the right; third row left: a plan top view.

In the illustrated embodiment, the rotor 300 has a central shaft receiving member 302, and at the low pressure input region 304A, a first rotor blade portion 306A extends generally radially outward from the central shaft receiving member 302 and transitions (smoothly) via a rounded edge 312 into a second rotor blade portion 306B, the second rotor blade portion 306B generally coaxial with the central shaft receiving member 302 and extending along the central shaft receiving member 302 toward the high pressure output region 304B. During operation, the first and second rotor blade portions 306A and 306B and the rounded edge 312 deflect gaseous matter generally in a near-axial and radially-inward direction. In this embodiment, the proximal axial extension X of the second rotor blade section 306B is greater than the radial extension R of the first rotor blade section 306A.

The rotor blades in the first rotor blade section 306A are inclined with respect to a first plane P1 perpendicular to the central shaft receiving member 302, and the rotor blades in the second rotor blade section 306B are inclined with respect to a generally hollow cylindrical envelope profile C1 generated by the second rotor blade section 306B.

Third rotor blade portion 306C extends generally radially outward from central shaft receiving member 302 and is connected to second rotor blade portion 306B at a location between low pressure input region 304A and high pressure output region 304B for enhanced mechanical stability. During operation, the third rotor blade section 306C deflects gaseous matter generally in the proximal axial direction. The rotor blades in the third rotor blade portion 306C are inclined with respect to a second plane P2 perpendicular to the central shaft receiving member 302.

Adjacent ones of the first, second, and third rotor blade sections 306A, 306B, and 306C generally overlap one another such that there is little to no direct line of sight from the interior to the exterior, so as to prevent gaseous matter that has entered the interior from escaping or otherwise exiting in directions other than toward the high pressure output region 304B.

An annular support structure 308 is connected to the distal end of the rotor blade in the second rotor blade section 306B to enhance mechanical stability.

The central shaft receiving member 302 includes a hollow receiver 314 for receiving a drive shaft (not shown) that is capable of rotating the central shaft receiving member 302. The central shaft receiving member 302 also includes thickened sections 310A and 310B, the thickened sections 310A and 310B being associated with (corresponding) ones of the first and third rotor blade portions 306A and 306C, respectively, the first and third rotor blade portions 306B and 306C having rotor blades extending generally radially, the thickened sections 310A and 310B flaring (frustoconical) from the high pressure output region 304B to the low pressure input region 304A to impart additional momentum in a direction toward the high pressure output region 304B to gaseous matter deflected from the second rotor blade portion 306B in a generally radially inward direction.

In the illustrated embodiment, the number of rotor blades in the first, second, and third rotor blade sections 306A, 306B, and 306C is odd to reduce resonant vibration during operation to further stabilize the structure.

Compared to the embodiment of fig. 2, the rotor 300 has a smaller mass to be rotated, in particular due to the rounded top edge 312, and still achieves an even higher pump speed.

Fig. 4A (and fig. 4B) depict yet another example of a novel cage rotor design in several views. Left side of the first row: a bottom plan view supplemented by a side cross-sectional view on the right and an isometric cross-sectional view further to the right; left side of second row: a plan side view supplemented by a cutaway plan top view and an isometric view of the right side; third row left: a plan top view.

In the illustrated embodiment, the rotor 400 has a central shaft receiving member 402, and at the low pressure input region 404A, a first rotor blade portion 406A extends generally radially outward from the central shaft receiving member 402 and transitions (smoothly) via a rounded edge 412 into a second rotor blade portion 406B, the second rotor blade portion 406B extending generally coaxially with the central shaft receiving member 402 and along the central shaft receiving member 402 toward the high pressure output region 404B. During operation, first and second rotor blade portions 406A and 406B and rounded edges 412 deflect gaseous matter generally in a proximal-axial and radially-inward direction.

The rotor blades in the first rotor blade section 406A are inclined with respect to a first plane P1 perpendicular to the central shaft receiving member 402, and the rotor blades in the second rotor blade section 406B are inclined with respect to a generally hollow cylindrical envelope profile C1 generated by the second rotor blade section 406B.

In the illustrated example, the rotor blades in the second rotor blade section 406B are helically twisted (moderately) along the generally hollow cylindrical envelope profile C1 generated by the second rotor blade section 406B to deflect gaseous matter from the second rotor blade section 406B generally in a proximal-axial and radially-inward direction.

The third rotor blade portion 406C extends generally radially outward from the central shaft receiving member 402 and is connected to the second rotor blade portion 406B at a location between the low pressure input region 404A and the high pressure output region 404B for enhanced mechanical stability. During operation, the third rotor blade section 406C deflects gaseous matter generally in the proximal axial direction. The rotor blades in the third rotor blade section 406C are inclined with respect to a second plane P2 perpendicular to the central shaft receiving member 402.

Adjacent rotor blades in the first, second, and third rotor blade portions 406A, 406B, and 406C and the rounded edges 412 generally overlap one another such that there is hardly any direct line of sight from the interior to the exterior, so as to prevent gaseous matter that has entered the interior from escaping or otherwise exiting in directions other than toward the high pressure output region 404B.

The annular support structure 408 is connected to the distal end of the rotor blade in the second rotor blade section 406B to enhance mechanical stability.

In the illustrated embodiment, the proximal axial extension X of the second rotor blade section 406B is equal to or greater than the radial extension R of the first rotor blade section 406A.

The central shaft receiving member 402 includes a hollow receiver 414 for receiving a drive shaft (not shown) that is capable of rotating the central shaft receiving member 402. The central shaft receiving member 402 also includes thickened sections 410A and 410B, the thickened sections 410A and 410B being associated with (corresponding ones) of the first and third rotor blade portions 406A and 406C, respectively, the first and third rotor blade portions 406B and 406C having rotor blades extending generally radially, the thickened sections 410A and 410B flaring (frustoconical) from the high pressure output region 404B to the low pressure input region 404A to impart additional momentum in a direction toward the high pressure output region 404B to gaseous matter deflected from the second rotor blade portion 406B in a generally radially inward direction.

In the illustrated embodiment, the number of rotor blades in the first, second and third rotor blade sections 406A, 406B, 406C is odd to reduce resonant vibration.

Fig. 4B shows the embodiment of fig. 4A with less detail. For clarity, all but two of the first, second, and third rotor blade portions 406A, 406B, 406C are removed.

The previous fig. 1-4 describe an embodiment of a mechanically stabilized cage rotor. Stress simulations by computer program showed that: the maximum displacement of the rotor blades in the near-axis rotor blade section at 60000RPM is less than 0.1 mm and does not crack the blades, which means higher mechanical integrity. The model is based on the following cage-like structure: the cage has a diameter of 60mm (2 x R) built around two radial rotor blade sections, wherein the tips of the proximal rotor blades are connected to each other by an annular support. The axial height X is set to 42 mm. Assuming the material is 6075 aluminum (T-6 aircraft aluminum), the total weight of the exemplary rotor is approximately 60 grams.

Fig. 5A shows, by way of example, a novel rotor design concept in a turbomolecular pump 516 used in a mass spectrometer. The rotor 500 in the illustrated embodiment may take the shape of any of the examples depicted in fig. 2, 3, and 4A. The presently shown rotor design is largely identical to the rotor design in fig. 4A.

As is apparent from the upper drawing in fig. 5A, the turbomolecular pump 516 has a fixed frame structure near the rotor 500, which comprises a plurality of arcs 520, the plurality of arcs 520 converging at the end of a central shaft receiving member in a bearing (not shown) located at the low pressure input region 504A, the low pressure input region 504A coinciding with the volume of a substantially gas tight compartment 530 to be evacuated in the receiver of the mass spectrometer. The fixed frame structure also includes a flange or step 528 spaced from the low pressure input region 504A, and a plurality of arcs 520 are connected to the flange or step 528 for mechanical support. The flange 528 abuts closely the outside of the bottom wall of the compartment 530 where the turbomolecular pump 516 is mounted and helps seal the assembly.

As is apparent from the lower drawing in fig. 5A, only one compartment 530 of the receiver of the mass spectrometer is shown for clarity (although there may be more than one compartment, some or all of which must be kept below atmospheric pressure). The cut-outs at the top and side walls allow unobstructed viewing of the interior. In this example, the compartment 530 comprises two mass filters 532A, 532B, e.g. quadrupole mass filters, arranged parallel to each other on different sides of the compartment 530. The two mass filters 532A, 532B may be part of a triple quadrupole mass analyser (the concept of which is well known to those skilled in the art). As shown by way of example in fig. 6A of US 8,618,473B 2 (which may be incorporated herein by reference in its entirety), the two mass filters 532A, 532B may comprise straight portions of a U-shaped ion path (not identified) that is directed out of and through a first one of the two mass filters, to and through a second one of the two mass filters via a generally arcuate collision cell (not shown) that is supplied with a neutral gas to assist in collision-induced dissociation upon ion implantation, and is thus optically connected with the outlet and inlet ions of each of the two mass filters 532A, 532B. During operation, the compartment 530 is maintained at a pressure substantially lower than ambient atmospheric pressure, for which reason the compartment 530 needs to be fluidly connected with the pump 516. The main gas load in this triple quadrupole design originates from the ion source region and the collision cell (both not shown). A portion of the gas loading may come from surface outgassing.

Conventional turbomolecular pumps are mounted on such compartments that are substantially flush with the first rotor stage at the low pressure input, which largely sinks into the floor or side walls of the receiver (see the schematic of the upper diagram of fig. 1), and are to be evacuated, but the novel rotor and turbomolecular pump design of the present invention deviates from this conventional approach in the following respects: the pump 516 is mounted at the compartment 530 such that the rotor 500 and a substantially extended proximal rotor blade portion of the rotor 500 substantially protrudes into the compartment 530. This enables a pumping action in the proximal axial direction as well as in the radially inward direction, which in the example shown is over the entire circumference of the 360 ° pump rotor. The embodiment shown in the lower drawing of fig. 5A enables the construction of a compartment 530 having a particularly fine size, thereby significantly reducing the size and weight, and at the same time increasing the pump speed.

Furthermore, in the embodiment shown in the lower diagram of fig. 5A, the rotor 500 protrudes to be directly exposed to gaseous species escaping or otherwise exiting the two mass filters 532A, 532B, which may further reduce the risk of cross-contamination between the two mass filters 532A and 532B. It goes without saying that instead of the two mass filters 532A, 532B, other types of mass analyzers, such as for example, as non-limiting examples, time-of-flight drift tubes, for example

(Thermo Fisher Scientific) and other Goldden-type mass analyzers, 2D or 3D ion traps, and/or ionsA cyclotron resonance cell. Those skilled in the art will recognize that the turbomolecular pump 516 protruding from the bottom wall of the compartment 530 at the receiver is shown by way of example only. The turbomolecular pump 516 may also be positioned at any suitable one of the other boundary walls of the compartment 530, for example at a top wall that is not shown for clarity.

Fig. 5B depicts how a turbomolecular pump with the features of a novel rotor design (e.g., taken from any of the embodiments shown in fig. 2, 3, and 4A), such as the turbomolecular pump shown in the upper diagram of fig. 5A, can be used to evacuate a drift tube of a time-of-flight mass analyzer (OTOF) with orthogonal acceleration in this example. The general concept of OTOF mass spectrometers is well known to those skilled in the art and need not be discussed further herein.

In the illustrated embodiment, ions to be analyzed are supplied to the time-of-flight analyzer from an ion source (not shown) that is fluidly attached and the ions are optically attached to the lower leg ("horizontal leg") 534 of the L-shaped receiver. A multipole system 536 located in the lower leg 534 may be used to direct ions through the lower leg 534 of the receiver to a main compartment ("vertical leg") 538 of the receiver, the main compartment 538 behaving primarily as a drift tube of a time-of-flight analyzer with orthogonal acceleration and containing a pulse generator 540 unit for orthogonal acceleration and a reflectron stage 542, the reflectron stage 542 decelerating and re-accelerating the orthogonally accelerated ions along a generally V-shaped trajectory onto a detector 544 located at a position slightly laterally displaced from the pulse generator unit 540.

Three turbomolecular pumps 516A, 516B, and 516C are shown extending along the elongated main compartment 538, with the turbomolecular pumps 516A, 516B, and 516C having a novel rotor design and being evenly distributed to provide substantially uniform vacuum conditions throughout the length of the main compartment 538. The number of pumps 516A, 516B and 516C is shown here by way of example as three. Different numbers of pumps, such as one pump, two pumps, or four or more pumps, are also contemplated and should be considered within the scope of the present invention. Those skilled in the art will also recognize that if there is more than one pump, the pumps need not be located on the same side of the vacuum receiver, but may be mounted on different (opposite and/or adjacent) sides as appropriate.

Each of the pumps 516A, 516B and 516C is mounted at the main compartment 538 such that the respective proximal rotor blade portion of the pump protrudes substantially into the main compartment 538, thereby facilitating pumping action in the proximal direction as well as the radial direction as viewed from the axis of the respective turbomolecular pump 516A, 516B and 516C. To save cost, all three turbomolecular pumps 516A, 516B, and 516C may share a conventional high pressure turbine stage (e.g., at about 10 a)^-4Torr (-1.3X 10)^-2Pascal)) that may be implemented at the central turbomolecular pump 516B of the three illustrated turbomolecular pumps. As shown by way of example in fig. 5B, the fluid connection between the three pumps 516A, 516B and 516C may then be ensured by auxiliary gas-tight hollow compartments 546 at the mounting sides of the pumps 516A, 516B and 516C. For clarity, the actual open port for exhaust of the pump configuration is not shown.

The embodiment shown in fig. 5B enables the construction of a main compartment 538 with particularly fine dimensions, such as the main compartment shown by way of example in the measurement view on the right, where the measurement values are shown in millimeters.

Fig. 6A shows a multi-port cage rotor design in several different views. Left panel: a cross-sectional side view; the middle part: a plan side view; right panel: an isometric view.

The embodiment of the turbomolecular pump 616 shown in fig. 6A has multiple rotor stages 600A and 600B. The first rotor stage 600A near the low pressure input region 604A may be implemented, for example, by any of the rotor embodiments described in conjunction with fig. 2, 3, and 4A. The present figure shows a first rotor stage 600A having the configuration described in connection with the example of fig. 4A.

Further, the second rotor stage 600B of the rotor is constructed based on the same principles as described with reference to the previous rotor embodiment (e.g., the rotor in any of the rotor embodiments of fig. 2, 3, and 4A), and therefore, additional description is not required herein. The second rotor stage 600B includes two radial rotor blade sections connected to a proximal rotor blade section having a height (or proximal dimension) that is lower than the height of the proximal rotor blade section used in the first rotor stage at the low pressure input region. The stationary frame structure or housing at the second downstream rotor stage 600B is provided with lateral port openings 648 so that the proximal rotor blade portions in the second rotor stage 600B can be fluidly connected with the compartments to be evacuated to a pressure level different from and above the value maintained by the first rotor stage 600A at the top of the illustrated turbomolecular pump 616.

The turbomolecular pump of fig. 6A has a fixed frame structure comprising a plurality of arcs 620, the plurality of arcs 620 converging at an end of the first central shaft receiving member 602A near the low pressure input region 604A in a bearing 622, which bearing 622 may be a magnetic bearing with a plurality of permanent magnets or a ball bearing comprising a plurality of ceramic balls with ultra-smooth surfaces. The ball bearing can be lubricated by special lubricating grease with extremely low vapor pressure. In addition, the fixed frame structure includes a flange or step 624 spaced apart from the low pressure input region 604A, and the plurality of arcs 620 are connected to the flange or step 624. Specifically, the flange or step 624 serves to mount the turbomolecular pump 616 to a chamber that is to be evacuated during operation, and to seal the connection.

The second central shaft receiving member 602B of the second rotor stage 600B has a hollow receptacle for receiving the drive shaft 626 (just like the first central shaft receiving member of the first rotor stage 600A, although not indicated in this figure), which drive shaft 626 is capable of rotating the second central shaft receiving member 602B (together with the first central shaft receiving member in the first rotor stage 600A) during operation.

The second central shaft receiving member 602B may flare in a section-wise direction from the high pressure output region 604B to the low pressure input region 604A to impart additional momentum in a direction toward the high pressure output region to gaseous species deflected generally radially inward from the proximal rotor blade portions in the second rotor blade portion 600B.

A conventional rotor-stator stage 628 with radially extending interdigitated rotor-stator blades is located between a first rotor stage 600A (with a rotor as disclosed in any of the embodiments of fig. 2, 3 and 4A) and a second rotor stage 600B (with a rotor that may be identically configured according to the principles disclosed in any of the embodiments of fig. 2, 3 and 4A) along a central drive shaft 626 that is received in the hollow receptacles of first and second central shaft receiving members 602A and 602B, respectively, and actuated by the motor.

Fig. 6B illustrates, by way of example, the use of a multiport turbomolecular pump 616 as described above in a mass spectrometer.

The mass spectrometer has a receiver comprising at least two adjacent compartments, of which two compartments 630A, 630B are shown. During operation, the compartments 630A, 630B will be maintained at slightly different pressures that are substantially below ambient atmospheric pressure, e.g., compartment 630A is for an ultra-high vacuum (e.g., about 10A)^-7Below the support; 1.3X 10^-5Pascal) mass filter. The lower compartment 630B may contain an ion source, such as an electrospray source, a chemical ionization source, or an electron ionization source, all of whose principles are well known to those skilled in the art, and the lower compartment 630B may be maintained at a higher pressure level, e.g., about 10^-4Torr (-1.3X 10)^-2Pascal). For example, the turbomolecular pump of the multi-port configuration 616 described in connection with fig. 6A (and having a rotor that may be implemented according to one of the examples shown in any of fig. 2, 3 and 4A) is mounted at two adjacent compartments 630A, 630B, such that the first rotor stage 600A and its associated proximal rotor blade section substantially protrude into a first compartment 630A of the at least two adjacent compartments, and the second rotor stage 600B and its associated proximal rotor blade section are fluidly connected via a port opening with a second compartment 630B of the at least two adjacent compartments, the second compartment 630B being maintained at a pressure that is slightly higher than the pressure in the first compartment 630A, as the first compartment 630A is fluidly connected with the pump 616 closer to the high pressure exhaust section.

Fig. 6B shows an example of a multi-port turbo-molecular pump 616 that includes two rotor stages 600A, 600B with respective port openings 648. It will be understood by those skilled in the art that the concept of a multi-port turbomolecular pump comprising a novel rotor design can be extended to more than two novel rotor stages (in addition to conventional rotor-stator stages) with corresponding port openings, as deemed appropriate by practitioners in the art.

The rotor stage(s) in the embodiments of any of the foregoing fig. 1-6 may be made of a stable metal, such as aluminum, magnesium, titanium, or alloys thereof. In particular, the rotor stage(s) may be fabricated by additive manufacturing (e.g., powder fusion) or integral casting, for example, using a stable material such as titanium aluminide (TiAl).

Aluminum and titanium are the preferred metals for additive manufacturing of metal parts and have extremely high mechanical strength and temperature resistance. Additive manufacturing has the additional advantage that very unusual alloys with properties different from the standard alloy can be used.

As an example of a low weight, high mechanical strength material, γ TiAl, an intermetallic compound of aluminum and titanium (titanium aluminide), has excellent mechanical properties as well as oxidation and corrosion resistance at high temperatures (over 600 degrees celsius). γ TiAl is used in blades of modern aircraft turbine engines because γ TiAl has an excellent thrust-to-weight ratio. Additive manufacturing can produce parts composed of such alloy intermetallic compounds.

The present invention has been shown and described above with reference to a number of different embodiments thereof. However, it will be apparent to one skilled in the art that various aspects or details of the invention may be changed or combined in any combination without departing from the scope of the invention. In general, the foregoing description is for the purpose of illustration only and is not intended to be limiting, the invention being defined only by the appended claims and including any equivalents as appropriate.