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US20080095634A1 - Multi-stage turbine using steel and aluminum blades - Google Patents

Multi-stage turbine using steel and aluminum blades Download PDF

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Publication number
US20080095634A1
US20080095634A1 US11/859,611 US85961107A US2008095634A1 US 20080095634 A1 US20080095634 A1 US 20080095634A1 US 85961107 A US85961107 A US 85961107A US 2008095634 A1 US2008095634 A1 US 2008095634A1
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US
United States
Prior art keywords
aluminum
turbine
fan blade
steel
stage fan
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US11/859,611
Inventor
Joseph W. Kieffer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Titan Tool Inc
Original Assignee
Titan Tool Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Titan Tool Inc filed Critical Titan Tool Inc
Priority to US11/859,611 priority Critical patent/US20080095634A1/en
Assigned to TITAN TOOL, INC. reassignment TITAN TOOL, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KIEFFER, JOSEPH W.
Publication of US20080095634A1 publication Critical patent/US20080095634A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • F04D17/125—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors the casing being vertically split
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/06—Adaptations for driving, or combinations with, hand-held tools or the like control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys

Definitions

  • the present invention is directed to turbines suited for application to paint sprayers, more particularly, to HVLP (High Volume, Low Pressure) type sprayers.
  • Current turbine technology for HVLP paint spraying equipment uses aluminum blades for each stage of the turbine for turbines of between one and three stages. Steel blades are used for each stage of four stage turbines because of the higher pressures and temperatures present in the four stage version. Additionally, such higher performance turbines have been limited to 4 stages due to the large overhung load of the 4-steel blades. Because of the steel blade construction, these turbines are extremely difficult to balance. The extra weight changes the critical vibration frequency to be very close to the operating speed (RPM) of the turbine motor during normal operation. If the turbine is not properly balanced, the vibration harmonics can cause premature wear and even destroy the inboard bearing.
  • RPM operating speed
  • conventional aluminum is to be understood to be non-aircraft grade aluminum, in contrast to aircraft grade aluminum which, typically, has one or more alloying elements added to change the characteristics of the aluminum.
  • alloying elements include: copper (in 2xxx series aluminum), magnesium and silicon (in 6xxx series aluminum), and zinc (in 7xxx series aluminum).
  • aircraft grade aluminum refers to those aluminum alloys which are capable of withstanding the high temperatures and pressures (loads) at the outlet stage(s) of HVLP turbines.
  • aircraft grade aluminum may be suitable for the high temperatures and pressures at the outlet stage(s) of HVLP turbines, such materials have the disadvantage of increased cost over non-aircraft grade aluminum.
  • non-aircraft grade aluminum is 1xxx series aluminum which has no major alloying element and has a minimum aluminum content of 99%.
  • Aircraft grade aluminum has another disadvantage that it is not readily recyclable because of the presence of the alloying element(s). It is thus desirable to use non-aircraft grade aluminum in the inlet stage(s) of HVLP turbines with its cost and recyclable advantages, while avoiding the disadvantages of aircraft grade aluminum in the outlet stage(s) of such turbines.
  • a simultaneous solution to both the critical frequency and overhung load issues for a five (or more) stage turbine is to make the first or inlet stages out of non-aircraft grade aluminum and the last or outlet stages out of steel.
  • the first stages are the farthest outward from the intermediate bearing (located between the motor and fan section).
  • Making the first stages of the fan section out of non-aircraft grade aluminum greatly reduces the overhung load, since such aluminum is roughly 1 ⁇ 3 the weight of steel.
  • the higher (or outlet) stages that require a material to stand up to the increased pressure and temperature are located closer to the intermediate bearing so their weight is not as significant as it would be if located further away from the intermediate bearing.
  • the combination of steel blades at the outlet end and non-aircraft grade aluminum blades at the inlet end of the turbine is effective to place the steel blades at the region of the turbine having higher pressures and temperatures.
  • the blades at the outermost end of the shaft that cause the most overhung load are made of non-aircraft grade aluminum where they are subjected to lower pressures and temperatures.
  • FIG. 1 is a perspective view of a prior art HVLP turbine assembly in its housing.
  • FIG. 2 is a view of the prior art turbine assembly and housing of FIG. 1 , shown partly in section.
  • FIG. 3 is an exploded view of the prior art turbine assembly of FIG. 2 .
  • FIG. 4 is a side view of a turbine of the present invention, cut away to illustrate certain aspects of the present invention.
  • FIGS. 1-3 a prior art HVLP turbine assembly 10 and housing 11 may be seen.
  • a single stage reverse axial flow turbine 40 is close coupled to a four stage conventional flow tangential discharge turbine 41 .
  • the arrangement shown in FIGS. 1-3 is from U.S. Pat. No. 5,639,222, the entire contents of which are hereby expressly incorporated by reference.
  • apparatus 10 is capable of providing a five stage turbine, but requires two motors ( 46 and 47 ), and is generally less efficient and more costly than an integral five stage fan section driven by a single motor.
  • FIG. 4 shows an integral five stage turbine 200 illustrating the present invention.
  • Turbine 200 has a fan stage 210 and an electric motor 212 coupled to the fan stage 210 to drive the fan stage 210 through rotation of a motor shaft 214 .
  • Shaft 214 is preferably supported by a motor bearing 216 and an intermediate bearing 218 .
  • the rotating fan blades in fan stage 210 are positioned outboard of the intermediate bearing 218 and thus constitute an overhung load on shaft 214 .
  • the first and second stage fan blades 220 are preferably made of non-aircraft grade aluminum.
  • the third stage fan blade may be made of non-aircraft grade aluminum (or steel if desired).
  • the fourth and fifth stage fan blades 224 are preferably made of steel. It is to be understood that the present invention may be extended to turbines with more stages, for example, six stages.
  • cooling air for motor 212 is drawn in along arrow 226 via motor air intake 228 .
  • the motor cooling air exits motor 212 in the direction of arrows 230 .
  • Turbine air enters a fan stage inlet 232 indicated by arrow 234 , and exits the fan stage 210 via a tangential exhaust 236 , in the direction of arrow 238 .
  • the invention may thus be seen to be a multistage turbine having at least one inlet stage fan blade formed of non-aircraft grade aluminum, and one or more intermediate stage fan blade formed of non-aircraft grade aluminum or steel (or a combination thereof), and one or more outlet stage fan blades formed of steel.
  • the invention is a five stage turbine having a first stage fan blade and a second stage fan blade each formed of non-aircraft grade aluminum, and a third stage fan blade formed of at least one of steel and non-aircraft grade aluminum, and a fourth stage fan blade and fifth stage fan blade formed of steel.
  • intermediate stage fan blade may be formed of both aluminum and steel, if desired, for its various components.
  • present invention may be practiced using aircraft grade aluminum for some or all of the aluminum parts of the present invention, with the consequent reduction or elimination of the advantages of using non-aircraft grade aluminum.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A multistage turbine having one or more input stage fan blades formed of aluminum and having one or more output stage fan blades formed of steel. One or more intermediate stages may be formed of aluminum or steel or a combination thereof.

Description

    CROSS REFERENCE TO RELATED APPLICATION
  • This application claims the benefit of U.S. Provisional Application No. 60/862,384 filed Oct. 20, 2006, the entire contents of which are hereby expressly incorporated by reference.
    • BACKGROUND OF THE INVENTION
  • The present invention is directed to turbines suited for application to paint sprayers, more particularly, to HVLP (High Volume, Low Pressure) type sprayers. Current turbine technology for HVLP paint spraying equipment uses aluminum blades for each stage of the turbine for turbines of between one and three stages. Steel blades are used for each stage of four stage turbines because of the higher pressures and temperatures present in the four stage version. Additionally, such higher performance turbines have been limited to 4 stages due to the large overhung load of the 4-steel blades. Because of the steel blade construction, these turbines are extremely difficult to balance. The extra weight changes the critical vibration frequency to be very close to the operating speed (RPM) of the turbine motor during normal operation. If the turbine is not properly balanced, the vibration harmonics can cause premature wear and even destroy the inboard bearing.
  • Each successive stage in a bypass turbine builds heat and pressure above the previous stages. Even though four stage turbines have found application in HVLP paint sprayer equipment, there continues to be a need for improved performance and reduced or controlled cost for turbines that exceed the performance of prior art four stage designs. A five (or more) stage turbine would be desirable, but making the stages out of steel would exacerbate the overhung load problem, and making the stages out of conventional aluminum is not feasible because the temperature and pressure at the outlet stage or stages of such a turbine design exceed the capability of conventional aluminum.
  • As used herein, conventional aluminum is to be understood to be non-aircraft grade aluminum, in contrast to aircraft grade aluminum which, typically, has one or more alloying elements added to change the characteristics of the aluminum. Of particular interest here are the various forms of aircraft grade aluminum which are able to withstand higher temperatures while maintaining sufficient strength in the intended application. Some examples of such alloying elements include: copper (in 2xxx series aluminum), magnesium and silicon (in 6xxx series aluminum), and zinc (in 7xxx series aluminum). Accordingly, as used herein, aircraft grade aluminum refers to those aluminum alloys which are capable of withstanding the high temperatures and pressures (loads) at the outlet stage(s) of HVLP turbines.
  • While aircraft grade aluminum may be suitable for the high temperatures and pressures at the outlet stage(s) of HVLP turbines, such materials have the disadvantage of increased cost over non-aircraft grade aluminum. (One example of non-aircraft grade aluminum is 1xxx series aluminum which has no major alloying element and has a minimum aluminum content of 99%.)
  • Aircraft grade aluminum has another disadvantage that it is not readily recyclable because of the presence of the alloying element(s). It is thus desirable to use non-aircraft grade aluminum in the inlet stage(s) of HVLP turbines with its cost and recyclable advantages, while avoiding the disadvantages of aircraft grade aluminum in the outlet stage(s) of such turbines.
    • BRIEF SUMMARY OF THE INVENTION
  • A simultaneous solution to both the critical frequency and overhung load issues for a five (or more) stage turbine is to make the first or inlet stages out of non-aircraft grade aluminum and the last or outlet stages out of steel. The first stages (the inlet stages) are the farthest outward from the intermediate bearing (located between the motor and fan section). Making the first stages of the fan section out of non-aircraft grade aluminum greatly reduces the overhung load, since such aluminum is roughly ⅓ the weight of steel. The higher (or outlet) stages that require a material to stand up to the increased pressure and temperature are located closer to the intermediate bearing so their weight is not as significant as it would be if located further away from the intermediate bearing.
  • The combination of steel blades at the outlet end and non-aircraft grade aluminum blades at the inlet end of the turbine is effective to place the steel blades at the region of the turbine having higher pressures and temperatures. The blades at the outermost end of the shaft that cause the most overhung load are made of non-aircraft grade aluminum where they are subjected to lower pressures and temperatures.
    • BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS
  • FIG. 1 is a perspective view of a prior art HVLP turbine assembly in its housing.
  • FIG. 2 is a view of the prior art turbine assembly and housing of FIG. 1, shown partly in section.
  • FIG. 3 is an exploded view of the prior art turbine assembly of FIG. 2.
  • FIG. 4 is a side view of a turbine of the present invention, cut away to illustrate certain aspects of the present invention.
    •  DETAILED DESCRIPTION OF THE INVENTION
  • Referring now to the Figures, and most particularly to FIGS. 1-3, a prior art HVLP turbine assembly 10 and housing 11 may be seen. In apparatus 10, a single stage reverse axial flow turbine 40 is close coupled to a four stage conventional flow tangential discharge turbine 41. The arrangement shown in FIGS. 1-3 is from U.S. Pat. No. 5,639,222, the entire contents of which are hereby expressly incorporated by reference. As may readily be noted, apparatus 10 is capable of providing a five stage turbine, but requires two motors (46 and 47), and is generally less efficient and more costly than an integral five stage fan section driven by a single motor.
  • FIG. 4 shows an integral five stage turbine 200 illustrating the present invention. Turbine 200 has a fan stage 210 and an electric motor 212 coupled to the fan stage 210 to drive the fan stage 210 through rotation of a motor shaft 214. Shaft 214 is preferably supported by a motor bearing 216 and an intermediate bearing 218. The rotating fan blades in fan stage 210 are positioned outboard of the intermediate bearing 218 and thus constitute an overhung load on shaft 214.
  • The first and second stage fan blades 220 are preferably made of non-aircraft grade aluminum. The third stage fan blade may be made of non-aircraft grade aluminum (or steel if desired). The fourth and fifth stage fan blades 224 are preferably made of steel. It is to be understood that the present invention may be extended to turbines with more stages, for example, six stages.
  • In operation, cooling air for motor 212 is drawn in along arrow 226 via motor air intake 228. The motor cooling air exits motor 212 in the direction of arrows 230. Turbine air enters a fan stage inlet 232 indicated by arrow 234, and exits the fan stage 210 via a tangential exhaust 236, in the direction of arrow 238.
  • The invention may thus be seen to be a multistage turbine having at least one inlet stage fan blade formed of non-aircraft grade aluminum, and one or more intermediate stage fan blade formed of non-aircraft grade aluminum or steel (or a combination thereof), and one or more outlet stage fan blades formed of steel.
  • In a preferred embodiment, the invention is a five stage turbine having a first stage fan blade and a second stage fan blade each formed of non-aircraft grade aluminum, and a third stage fan blade formed of at least one of steel and non-aircraft grade aluminum, and a fourth stage fan blade and fifth stage fan blade formed of steel.
  • It is to be understood that the intermediate stage fan blade may be formed of both aluminum and steel, if desired, for its various components.
  • It is to be further understood that the present invention may be practiced using aircraft grade aluminum for some or all of the aluminum parts of the present invention, with the consequent reduction or elimination of the advantages of using non-aircraft grade aluminum.
  • The invention is not to be taken as limited to all of the details thereof as modifications and variations thereof may be made without departing from the spirit and scope of the invention.

Claims (14)

1. A multistage turbine having at least one inlet stage fan blade formed of aluminum, and an intermediate stage fan blade formed of one of the materials of aluminum and steel, and an outlet stage fan blade formed of steel.
2. The multistage turbine of claim 1 wherein the intermediate stage fan blade is formed of both aluminum and steel.
3. The multistage turbine of claim 1 wherein at least the one inlet stage fan blade is formed of non-aircraft grade aluminum.
4. The multistage turbine of claim 1 wherein the at least one inlet fan blade is formed entirely of aluminum.
5. The multistage turbine of claim 1 wherein the aluminum is non-aircraft grade aluminum.
6. A five stage turbine having a first stage fan blade and a second stage fan blade each formed of aluminum, and a third stage fan blade formed of at least one of steel and aluminum, and a fourth stage fan blade and fifth stage fan blade formed of steel.
7. The turbine of claim 6 wherein the third stage fan blade is formed of both aluminum and steel.
8. The turbine of claim 6 wherein at least the first and second stage fan blades are formed entirely of aluminum.
9. The turbine of claim 6 wherein the aluminum is non-aircraft grade aluminum.
10. The turbine of claim 6 wherein at least the first and second stage fan blades and the third stage fan blade are each formed of non-aircraft grade aluminum.
11. The turbine of claim 6 wherein each fan blade formed of aluminum is formed of non-aircraft grade aluminum.
12. A High Volume Low Pressure turbine assembly having five stages delivering air to a paint spray gun atomizing paint, the turbine assembly comprising:
a) a plurality of inlet stage fan blades formed of non-aircraft grade aluminum; and
b) at least one outlet stage fan blade formed of steel.
13. The turbine assembly of claim 12 further comprising at least one intermediate stage fan blade formed of one of non-aircraft grade aluminum and steel.
14. The turbine assembly of claim 12 further comprising at least one intermediate stage fan blade formed of both non-aircraft grade aluminum and steel.
US11/859,611 2006-10-20 2007-09-21 Multi-stage turbine using steel and aluminum blades Abandoned US20080095634A1 (en)

Priority Applications (1)

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US86238406P 2006-10-20 2006-10-20
US11/859,611 US20080095634A1 (en) 2006-10-20 2007-09-21 Multi-stage turbine using steel and aluminum blades

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USD623663S1 (en) * 2009-10-30 2010-09-14 Wagner Spray Tech Corporation Fluid delivery system
USD623660S1 (en) * 2009-09-18 2010-09-14 Wagner Spray Tech Corporation Turbine
EP2809884A4 (en) * 2012-01-31 2016-07-13 United Technologies Corp ALUMINUM SURFACE

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479573A (en) * 1943-10-20 1949-08-23 Gen Electric Gas turbine power plant
US2847184A (en) * 1952-04-02 1958-08-12 Power Jets Res & Dev Ltd Bladed rotors and stators
US5040943A (en) * 1990-05-17 1991-08-20 Ametek-Lamb Electric Furnace blower housing and mounting bracket
US5059844A (en) * 1989-12-04 1991-10-22 Ametek-Lamb Electric Snap ring for electric motor
US5108199A (en) * 1990-12-17 1992-04-28 Ametek-Lamb Electric Motor bearing system
USD338208S (en) * 1991-06-07 1993-08-10 Wagner Spray Tech Corporation Turbine unit
USD365569S (en) * 1994-11-09 1995-12-26 Wagner Spray Tech Corporation Commercial turbine housing
US5556255A (en) * 1994-11-09 1996-09-17 Wagner Spray Tech Corporation Integral threaded turbine outlet
US5639222A (en) * 1995-07-06 1997-06-17 Wagner Spray Tech Corporation Close coupled series turbine mounting
US5702131A (en) * 1996-03-01 1997-12-30 Wagner Spray Tech Corporation Outlet fitting for a portable turbine
US20050022529A1 (en) * 2003-07-30 2005-02-03 Kabushiki Kaisha Toshiba Steam turbine power plant
US7096712B2 (en) * 2003-04-21 2006-08-29 Conocophillips Company Material testing system for turbines

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479573A (en) * 1943-10-20 1949-08-23 Gen Electric Gas turbine power plant
US2847184A (en) * 1952-04-02 1958-08-12 Power Jets Res & Dev Ltd Bladed rotors and stators
US5059844A (en) * 1989-12-04 1991-10-22 Ametek-Lamb Electric Snap ring for electric motor
US5040943A (en) * 1990-05-17 1991-08-20 Ametek-Lamb Electric Furnace blower housing and mounting bracket
US5108199A (en) * 1990-12-17 1992-04-28 Ametek-Lamb Electric Motor bearing system
USD338208S (en) * 1991-06-07 1993-08-10 Wagner Spray Tech Corporation Turbine unit
USD365569S (en) * 1994-11-09 1995-12-26 Wagner Spray Tech Corporation Commercial turbine housing
US5556255A (en) * 1994-11-09 1996-09-17 Wagner Spray Tech Corporation Integral threaded turbine outlet
US5639222A (en) * 1995-07-06 1997-06-17 Wagner Spray Tech Corporation Close coupled series turbine mounting
US5772711A (en) * 1995-07-06 1998-06-30 Wagner Spray Tech Corporation Filter blockage warning indicator
US5702131A (en) * 1996-03-01 1997-12-30 Wagner Spray Tech Corporation Outlet fitting for a portable turbine
US7096712B2 (en) * 2003-04-21 2006-08-29 Conocophillips Company Material testing system for turbines
US20050022529A1 (en) * 2003-07-30 2005-02-03 Kabushiki Kaisha Toshiba Steam turbine power plant

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USD623660S1 (en) * 2009-09-18 2010-09-14 Wagner Spray Tech Corporation Turbine
USD623663S1 (en) * 2009-10-30 2010-09-14 Wagner Spray Tech Corporation Fluid delivery system
EP2809884A4 (en) * 2012-01-31 2016-07-13 United Technologies Corp ALUMINUM SURFACE
US10655635B2 (en) 2012-01-31 2020-05-19 United Technologies Corporation Aluminum airfoil
US11231046B2 (en) 2012-01-31 2022-01-25 Raytheon Technologies Corporation Aluminum airfoil

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AS Assignment

Owner name: TITAN TOOL, INC., NEW JERSEY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:KIEFFER, JOSEPH W.;REEL/FRAME:019902/0861

Effective date: 20070919

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION