US3926535A - Gas turbine - Google Patents

Gas turbine Download PDF

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Publication number
US3926535A
US3926535A US480818A US48081874A US3926535A US 3926535 A US3926535 A US 3926535A US 480818 A US480818 A US 480818A US 48081874 A US48081874 A US 48081874A US 3926535 A US3926535 A US 3926535A
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United States
Prior art keywords
turbine
injector
blades
inlet
rotor
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Expired - Lifetime
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US480818A
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English (en)
Inventor
Jacques Morf
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.)
Rhone Poulenc Textile SA
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Rhone Poulenc Textile SA
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    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • F01D1/08—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially having inward flow
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles

Definitions

  • ABSTRACT A quiet, high-speed gas turbine having a peripheral supply groove in the housing to supply the motive gas from an injector inlet to a plurality of blades simultaneously.
  • the supply groove decreases in radial depth from the injector inlet to a point of extinction.
  • the turbine blades are arranged to meet the motive gas at a very low angle of attack ranging from parallel, on one leading surface, to 20 or less on the other leading surface.
  • the present invention relates to fluid-driven turbines and is concerned, more particularly, with a turbine driven by gaseous fluid at high rotational speeds with- I
  • a variety of gaseous fluid turbines have been tried with varying degrees of effectiveness.
  • One of the better turbines now available includes blades which are shaped for efficient conversion of the energy of the compressed, motive gas into useful torque and having a peripheral feed channel which decreases in depth and cross-sectional area from the motive gas inlet to a termination of extinction point and which opens to a plurality of blades.
  • This type of turbine is disclosed in French Pat. No. 1,063,861.
  • the fluid turbine In the high-speed winding of yarns upon bobbins, the fluid turbine is required to operate at extremely high speeds of from several thousand RPM up to one hundred thousand RPM. At such speeds, the motive gas may be fed at supersonic velocities and high pressures. The resultant noise level can be dangerous or, at least, unbearable so that the applicability and versatility of prior turbines in this service has been quite limited.
  • the changing diameter of the wound bobbin imposes a speed-change on the turbine, since it is usual to maintain a uniform speed of the periphery of the increasing diameter of winding to produce a uniform yarn speed. Therefore, the turbine is required to have a relatively flat torque curve through this range in which it must operate.
  • Highpressure turbines which work at inlet pressures of 3 to 8 bars, are best suited in this regard since they exhibit flat torque curves within their effective range.
  • these high-pressure turbines have a disadvantage in being quite inefficient at the lower speeds.
  • the preferred form of the present invention includes a bladed turbine wheel journalled in a closely-fitting rotor chamber in a housing, at least one injector in the housing for presenting motive gaseous fluid to the periphery of the turbine wheel, a supply channel in the housing and extended from the injector about the periphery of the rotor chamber a distance greater than the distance between adjacent blades of the turbine wheel, the supply channel being tapered over its length from adjacent the injector to a terminal point, the blades of the turbine wheel being open at the periphery of the wheel to receive motive fluid from the injector and the supply channel.
  • the blades of the turbine wheel are curvate and include both a generally convex wall and a generally concave wall, the radially-outer portion of the convex wall terminating in an intake section which is tangential to the motive gas stream, with the radially-outer portion of the concave wall terminating in an intake section which intersects the motive gas stream at an angle of less than 20 degrees, while the uniformly curved slots formed between adjacent blades include an arc of at least degrees from the intake zone to the slot outlet.
  • FIG. 1 is a sectional view of a preferred turbine housing according to the invention, taken transversely of the axis of the rotor;
  • FIG. 2 is a sectional view taken on lines 2-2 of FIG.
  • FIG. 3 is a sectional view similar to FIG. 2 and showing the rotor and drive shaft;
  • FIG. 4 is a view similar to FIG. 1, on an enlarged scale, partly cut away and showing the details of the new rotor blades of the preferred turbine;
  • FIG. 5 is a graph showing the comparative noise levels of the preferred turbine in comparison with prior art turbines at different frequencies.
  • the preferred form of turbine according to the present invention includes a bladed turbine wheel I mounted for rotation in a closefitting, rotor chamber 2 of a housing 3.
  • the housing 3 includes an annular supply chamber 4 receiving high-pressure gas via a supply inlet 5.
  • the annular supply chamber 4 communicates with the rotor chamber 2 by means of a pair of diametrically-opposed, tangentially-aligned, motive gas-stream injectors 6 and 7, respectively, and circumferential supply channels 8 and 9, respectively.
  • the axes of the peripheral injectors 6 and 7 are directed at between 80 and 90 to a radius of the rotor and rotor chamber so that the injectors are substantially tangential thereto.
  • the supply channels 8 and 9 gradually diminish in depth from a maximum, adjacent their respective gas stream injector 6 or 7, to a terminus or extinction point 10 and 11, respectively.
  • the extinction points 10 and 11 are spaced from the adjacent, downstream injector on the circumference of .the rotor chamber, preferably for an arc of at least 25, to form a sealing area between the two inlet zones.
  • the extinction point 10 of supply chamber 8 is circumferentially spaced from the gas stream injector 7 to provide a sealing area'l2
  • the extinction point 11 of supply channel 9 is spaced from the gas stream injector 6 to provide a similar, circumferential sealing area 13.
  • a single gas stream injector and supply channel may be employed or more than two such inlet zones may be selected, as long as adequate intermediate sealing zones are included.
  • the dynamic balance and simplicity of two diametrically-opposed injection-inlet zones is preferred with the supply channel extending over an arc of about 150, particularly for the small diameter turbines to be used in textile winding systems.
  • the bladed rotor l is drivingly mounted on a shaft 14 which is journalled by an anti-friction bearing 15 mounted on the housing 3 or a related structure 16.
  • the housing 3 has, on one side, an aperture 17 for re ceiving the shaft 14 therethrough.
  • the housing On its side opposite from the aperture 17,.the housing has a tubular extension 18 which terminates in an exhaust outlet 19 and which carries an exhaust dampener 20 therein.
  • the bladed rotor has a hub portion 21 having an inwardly-extending, concave outer surface 22 which permits discharge of the motive gas from between the blades into the tubular extension.
  • the rotor 1 includes a plurality of blades 23 which include opposite convex and concave surfaces 24 and 25, respectively.
  • the blades 23 are spaced apart to form a plurality of channels or slots 26 opening on the rotor periphery at slot-inlets 27 and opening inwardly toward the concave surface 22 of the hub 21 at slot-exits 28 to discharge the motive gas.
  • Each convex surface 24 of each of the blades is extended by a generally flattened area 29 which terminates in a curved inlet surface 30.
  • the area 29 is smoothly connected to the convex surface 24 and the curved inlet surface 30.
  • the curved inlet surfaces 30 are generally tangential to the axis of the injector at the point where the said axis meets the periphery of the rotor.
  • Each concave surface of each blade is smoothly connected to a convex area 31 which meets the surface at an angle of 20 degress or less. This angle called;
  • convex and concave surfaces of adjacent blades provide relatively wide, funnel-shaped slot-inlet zones for the smooth influx of the motive gas stream into the slots 26.
  • the slots 26 have curved zones beyond the flattened areas 29 and 31 and further extend along a substantially uniform curvature for an are 8" of at least 140 to enforce a prolonged, smooth deflection of the gas to derive the maximum potential of work from the motive gas stream before it is released, via the slot outlets 28, toward the exhaust outlet 19.
  • the turbine was operated under the following conditions:
  • the preferred turbine exceeded the 80 decibel limit only in the zone of the low frequency of about 330 Hz, which is still within the tolerance limit. This is, however, a ball-bearing noise corresponding to the frequency of the shaft, rather than being attributable to the turbine itself.
  • the total sound level of this turbine, integrated throughout the full range of form 0 Hz to 20,000 Hz, which is the generally accepted normal audible range, is 82.5 Db. or 77 Db.A.
  • the curve 11 makes an extreme excursion, with increasing frequencies, into the unpleasant and dangerous decibel levels, while that of the present invention stays below about 55 Db.
  • the contrasting curve ll does not return to this 55 Db. level until it reaches about 16,000 Hz, at which frequency the curve I of the preferred turbine of the invention has dropped to about 45 Db., about Db. lower.
  • the preferred turbine of the present invention is particularly effective in terms of power delivery and versatility.
  • the turbine set forth in the Example delivered an output of 90 watts at 16.000 rpm, with a total yield of 0.2.
  • the same size unit will deliver 750 watts at 30,000 rpm still without noise problems. Greater power outputs and speeds are anticipated, but an effort has not been made to determine the actual limits of this size of the preferred turbine.
  • curved inlet surfaces 30, the low-attack-angle inlet surfaces 31, the tangential injectors 6 and 7, the diminishing supply channels 8 and 9 and the 140 degree, curved slots 26 thus not only are particularly effective in converting the pressure and velocity of the compressed gas into useful torque, but also are effective in accomplishing these results in small diameter turbines without objectionable noise.
  • the turbine of the present invention avoids unnecessary shock or turbulent diversion of the motive gas stream, thereby utilizing the energy available in the compressed gas with a smooth transitional flow of the driving gas stream from the injector tangentially into the rotor chamber and at a minimum angle with respect to the inlet surfaces of the concavities of the blades.
  • a high-speed gas turbine comprising:
  • compressed gas injection means including at least one injector opening to said rotor chamber and aligned generally tangentially therewith,
  • said rotor having a plurality of blades, said blades defining a plurality of slots between adjacent blades, said slots each having an inlet zone on the periphery of the rotor and an outlet spaced radially inwardly from said inlet zone, each said blade including a convex side and a concave side, said slots being formed by adjacent pairs of concave and convex sides, each convex side having an inlet curved surface generally tangential to the axis of said injector at the point where said axis meets the periphery of the turbine rotor, each concave side having an inlet convex area converging toward the inlet surface of the respective convex side at an angle of less than 20.
  • each convex side includes a generally flat portion associated with its inlet surface and said generally flat portion and the inlet convex area of the adjacent blade being positioned to converge toward said curved portion of said slot.
  • the turbine of claim 3 including a plurality of injectors and a supply channel at each injector, the terminal point of each supply channel being spaced on the periphery of the rotor chamber from the peripheral position of the next injector and defining a sealing zone therebetween.
  • each said sealing zone extends over an arc of at least 25.
  • each injector is aligned with said rotor chamber at an angle of between and with respect to a radius of the rotor cham-

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)
  • Control Of Turbines (AREA)
US480818A 1973-07-17 1974-06-19 Gas turbine Expired - Lifetime US3926535A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7326439A FR2238382A5 (enrdf_load_stackoverflow) 1973-07-17 1973-07-17

Publications (1)

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US3926535A true US3926535A (en) 1975-12-16

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Application Number Title Priority Date Filing Date
US480818A Expired - Lifetime US3926535A (en) 1973-07-17 1974-06-19 Gas turbine

Country Status (7)

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US (1) US3926535A (enrdf_load_stackoverflow)
JP (1) JPS5556161Y2 (enrdf_load_stackoverflow)
CH (1) CH581782A5 (enrdf_load_stackoverflow)
DE (1) DE2434397C2 (enrdf_load_stackoverflow)
FR (1) FR2238382A5 (enrdf_load_stackoverflow)
GB (1) GB1474134A (enrdf_load_stackoverflow)
IT (1) IT1016207B (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006101411A1 (fr) * 2005-03-21 2006-09-28 Zakrytoe Aktsionernoe Obshchestvo 'nautchno-Issledovatelsky Tsentr Vikhrevoy Energetiki' Procede et installation de production d'energie
CN1519055B (zh) * 2003-01-30 2010-04-28 Gat传动技术有限公司 用于驱动快速旋转工具的涡轮
US10493472B2 (en) 2015-01-20 2019-12-03 Dürr Systems Ag Rotary atomizer turbine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2444792A1 (fr) * 1978-12-22 1980-07-18 Armines Turbine a vapeur a action
CH659198A5 (de) * 1983-04-20 1987-01-15 Findeva Ag Druckluft-vibrator mit turbinenantrieb.
DE10233199A1 (de) 2002-07-22 2004-02-05 Dürr Systems GmbH Turbinenmotor eines Rotationszerstäubers
JP4712427B2 (ja) * 2005-04-25 2011-06-29 Ｎｔｎ株式会社 静圧気体軸受スピンドル
US20180080324A1 (en) * 2016-09-20 2018-03-22 General Electric Company Fluidically controlled steam turbine inlet scroll

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US27448A (en) * 1860-03-13 horton
US578759A (en) * 1897-03-16 James f
US771759A (en) * 1904-01-21 1904-10-04 Charles A Backstrom Turbine running wheel.
US927534A (en) * 1908-06-19 1909-07-13 John Hormby Turbine.
US1277591A (en) * 1918-04-08 1918-09-03 William R Holliday Steam-turbine.
US2111136A (en) * 1934-05-21 1938-03-15 Bauer August Wing turbine unit
US2477681A (en) * 1945-08-17 1949-08-02 Electrolux Corp Electropneumatic power unit

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB729455A (en) * 1951-12-22 1955-05-04 Ulvsunda Verkst Er Aktiebolag Improvements in bearing devices for high speed spindles

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US27448A (en) * 1860-03-13 horton
US578759A (en) * 1897-03-16 James f
US771759A (en) * 1904-01-21 1904-10-04 Charles A Backstrom Turbine running wheel.
US927534A (en) * 1908-06-19 1909-07-13 John Hormby Turbine.
US1277591A (en) * 1918-04-08 1918-09-03 William R Holliday Steam-turbine.
US2111136A (en) * 1934-05-21 1938-03-15 Bauer August Wing turbine unit
US2477681A (en) * 1945-08-17 1949-08-02 Electrolux Corp Electropneumatic power unit

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1519055B (zh) * 2003-01-30 2010-04-28 Gat传动技术有限公司 用于驱动快速旋转工具的涡轮
WO2006101411A1 (fr) * 2005-03-21 2006-09-28 Zakrytoe Aktsionernoe Obshchestvo 'nautchno-Issledovatelsky Tsentr Vikhrevoy Energetiki' Procede et installation de production d'energie
US10493472B2 (en) 2015-01-20 2019-12-03 Dürr Systems Ag Rotary atomizer turbine

Also Published As

Publication number Publication date
JPS5556161Y2 (enrdf_load_stackoverflow) 1980-12-26
CH581782A5 (enrdf_load_stackoverflow) 1976-11-15
FR2238382A5 (enrdf_load_stackoverflow) 1975-02-14
DE2434397C2 (de) 1982-12-09
JPS5053538U (enrdf_load_stackoverflow) 1975-05-22
GB1474134A (en) 1977-05-18
DE2434397A1 (de) 1975-02-06
IT1016207B (it) 1977-05-30

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