US2141401A - Gas turbine - Google Patents

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Publication number
US2141401A
US2141401A US124407A US12440737A US2141401A US 2141401 A US2141401 A US 2141401A US 124407 A US124407 A US 124407A US 12440737 A US12440737 A US 12440737A US 2141401 A US2141401 A US 2141401A
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United States
Prior art keywords
rotor
cooling
blades
rim
anchors
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Expired - Lifetime
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US124407A
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English (en)
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Martinka Michael
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Individual
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Priority claimed from GB23413/38A external-priority patent/GB508436A/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Definitions

  • My invention relates to improvements in that class of rotary power producing machines, known as gas-combustionor explosive-turbines, in which an elastic working fluid-generally the gaseous combustion products of a mixture of fuel and air-violently flow at high velocity and temperature across the crown of blades of the rotary turbine wheel.
  • gas-combustionor explosive-turbines in which an elastic working fluid-generally the gaseous combustion products of a mixture of fuel and air-violently flow at high velocity and temperature across the crown of blades of the rotary turbine wheel.
  • Turbines of that class are distinguished from the more widely known class, of steam turbines by the unusually high range of temperatures, -ranglng considerably above 500 centigrade,at which the gaseous working medium reacts upon the blades of the rotary turbine wheel, briefly hereinafter called rotor", and by the greater working dimculties, generally accompanying, high temperatures, and calling for extraordinary precautionsviz. the provision of highly eflicier t cooling expedlents-in order to prevent destructive overstraining of the material, of which the rotor, its web and its blades are made.
  • the invention aims at providing a structurallyimproved gas-turbine, which can be safely worked at a higher speed, and which will show a higher efliciency, and a greater output in horsepower units per unit of weight of the turbine,-the ultimate object being tomake the improved gas-turbine lit for being used even on aeroplanesfzeppelin-air-ships. and kindred air craft, where the light weight of the motors and safety of their operation are. the predominant' considerations.
  • the invention employs gaseous currents for cooling the roots of the blades hereinafter called “shanks”; the latter are preferably elongated in radial direction, and are provided with recesses enclosing cooling chambers, and with anchors for fixing those blade structures in the rim of the turbine wheel.
  • Another salient feature or the invention is the provision of means for cooling the web of the turbine wheel by means of currents of a gaseous agent, recirculated in closed cycles of movement therearound, and of means for re-cooling the said gaseous currents in a specific graduated manner, namely in proportion to the respective amounts of heat to be dissipated at the said shanks of the blades and at the various zones of the web of the turbine wheel,and with the object of keeping the temperatures relatively low and practically constantand uniform throughout the whole'web.
  • Fig. 1 is a fragmentary section taken vertically through the turbine on line I-I in Fig. 2; I
  • Fig. 2 is aside elevation of the turbine, drawn on a smaller scale
  • FIGs. 3 and 4 show in enlarged scale the annular cooling ribs, enclosing the web of the turbine wheel, in cross section and in side elevation;
  • FIGs. 5 and 6 show perspectively the blades redesigned according to this invention
  • Figs. '1 and 8 are side elevations showing one of the blades with their shank as seen from either Fig. 12, which is a diagram, shows the development of temperatures within the blades, their shanks, the rim, web and nave of the turbine wheel.
  • the gas-turbine re-designed according to this invention essentially consists of:
  • the said radiators comprise two pairs of cooling ribs 35, 30', 32, 32', enclosing annular re- .cesses r, r (Fig. 3) of approximately circular cross sectional shape, and another pair of cooling ribs 34, 34', which jointly enclose an annular recess of substantially oval cross sectional shape 1'" and closely surround at both sides the respective cooling elements attached to and interal with the blades 3a, 3b of the turbine wheel referred to in detail hereinafter.
  • the radiator ribs 32, 32' and 3d, 3d are in direct contact with the cooling medium passing through the cooling jackets 42. 42' and M, 44, while the ribs 30, 30' and Jackets 40, 40' are spaced from each other, so as to indirectly act upon each other through radiation.
  • of the gas-turbine encloses the bladed turbine wheel or rotor, journalled therein at 25, 26 and comprising 4.
  • Toothed prongs 55 radially projecting from said web 40, the lateral faces or flanks of said prongs extending parallel to the axis of the turbine wheel;
  • the said shanks 4a., 4b, provided and arranged according to this invention and in contradistinction to prior art gas-turbines intermediate the blades and their roots, are so designed as to act at the same time as blade carriers. and blade cooling and spacing members, namely to keep the blades 3a, 3b-being the hottest portion of those blade structuresa considerable distance apart from the rotor rim, its prongs 55, and the rotor web,thus providing a zone of ample width, which is not integral with the rotor rim,
  • a salient feature of said blade structures consists therein, that they are fitted together and into their places at the rotor rim with such allowances as to their width, that they are capable of individually expanding to a predetermined extent. Chos n as to prevent excessive "heat stresses of the character described in the preamble, which would occur, if the blade structures were fitted rather tightly and under considerable initial pressure against each other, and into their places between the prongs 55 of the turbine wheel.
  • the'said shanks 4a, 4b are preferably of double T or I cross sectional shape, best seen in Fig. 10 at the right, namely they are formed with lateral walls having holes 40, 4c, 4d, 4d, and recesses 4e, 4e, so designed, that every two blade structures adjacently disposed to each other present a cooling chamber having an intake port at 4e, 4e, and two discharge holes 40, 4c.
  • said lower flanges are formed at their bottom with curved faces 30 for deflecting the cooling air, discharged through the holes 4c, 40, 4d, 4d.
  • the heated gas discharged through the holes 40, 4c, 4d, 4d is intensely re-cooled on travelling take ports 55' and through the channels 52';
  • the said cooling ribs 30, 30", 32, 32', and in turn the currents of gas circulating therebetween are recooled, substantially in proportion to the decreasing amounts of heat to be dissipated by the cooling jackets 42, M, which are in direct contact with the ribs 32, 32',-and by the cooling Jackets 40, Mi arranged at a distance from the ribs 30, 30', so as to indirectly act upon each other through radiation.
  • guide elements in the form of twisted strips of sheet steel, of which a short piece is shown at 60 in Fig. 4. may be provided within the recesses enclosed by the ribs 86, 8b, 32, 32', in order to cause the annular currents of cooling gas, travelling in circumferential direction, to attain at the same time a twisting motion, and to thereby enhance the emciency of both the primary and secondary cooling medium.
  • the secondary cooling medium-preferabiy water- should be positively circulated by a pump P (Fig. 2) through the cooling jackets in the direction of the arrows i-o and i'--o', and be recooled by a radiator R or other appropriate means known per se and shown in Fig. 2: 3
  • the coolest water should enter the jackets M, M opposed to the shanks do, db of the turbine blades, in order to most eilectively cool the hottest part of the rotor; and should thence pass through the jackets t2-4it, and iT-til', in such manner, that the cooling effect is graduated according to local heat conditions at the rotor rim and web.
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor.
  • the combination with a crown of blade structures. having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,--of primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated.
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting. said rotor, the combination with a crown of blade structures, fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,-of primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,-and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated,- said shanks being of I cross sectional shape so as to present recesses at opposed sides so interengaging each other, that every two adjacently disposed blade structures enclose a cooling chamber.
  • a gas-turbine having a bladed rotor and a housing, enclosing and assault.
  • rotor the combination with a crown of blade structure having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades prope'n-oi primary coolingmeans, employing a pinralityof gaseous-currents re-circulated in closed cycles oi movement through said hollow s and around the rim and web of the rotor,-and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated, said shanks being of I cross sectional shape so as to present recesses at opposed sides so lnterensa ng each other, that every two adiacently disposed blade structures enclose a cooling chamber,-tbe latter being provided with intake ports and discharge holes at their lower and upper ends.
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow sha arranged intermediate the said anchors and the blades proper,-o primary cooling means, elmploying a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,-andsecondary cooling means for recooling the respective gaseous currents in pro- W portion to the amount of heat to be locally dissipated,-the rotor rim presenting toothed prongs, spaced from each other for engagement with pairs of said anchors of the blades.
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having'anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,--of primary cooling means, employing a plurality of gaseous currents re circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,-and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated,--the said anchors of the blades being the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,-of primary cooling means, em-
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades, proper,--of primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated,--the said primary cooling means comprising a plurality of cooling ribs, the front faces of which being opposed to said shanks and anchors of the blade structures, and to the rim and web of the rotor respectively, while their rear faces are opposed to the said secondary cooling means.
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,of primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around'the rim and web of the rotor,and secondary cooling means for recooling the respective gaseous currents in proportion to the amount of heat'to be locally dissipated, the saidprimary cooling means comprising a plurality of cooling ribs, the front faces of which being opposed to said shanks and anchors of the blade structures, and to the rim and web of the rotor respectively, while their rear faces are opposed to the said secondary cooling means,--the latter employing a liquid cooling agent.
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,-if primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,- and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated, the said primary cooling means comprising a plurality of cooling ribs, the front faces of which being opposed to said shanks and anchors of the blade structures, and to the rim and web of the rotor respectively, while their rear faces are opposed to the said secondary cooling means, the latter employing a liquid cooling agent,and comprising a plurality of ring shaped jackets, through which said liquid
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,of primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow -shanks and around the rim and web of the opposed tosaid shanks and anchors of the blade structures, and to the rim and web of the rotor respectively, while their rear faces are opposed to the said secondary cooling means, the latter employing a liquid cooling agent, and comprising a plurality of 'ring shaped jackets, through which said liquid cooling agent circulates-the outermost set of cooling ribs, opposed to the peripheral zone of the turbine rotor being integral with their respective cooling jackets, while the innermost cooling ribs, opposed to the web of the rotor, are spaced
  • a gas-turbine having a bladed rotor and a housing, enclosing and supportingsaid rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the blades proper,of primary cooling means, employing a plurality of gaseous currents re-circulatedi in -closed cycles of movement through said hollow shanks and around the rim and web of the rotor,- and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated, the said primary cooling means comprising a plurality of cooling ribs, the front faces of which being opposed to said shanks and anchors of the blade structures, and to the rim and web of the rotor respectively, while their rear faces are opposed to the said secondary cooling means,--the cooling ribs, opposed to the rotor rim and web enclosing annular
  • a gas-turbine having a bladed rotor and a housing, enclosing and supporting said rotor, the combination with a crown of blade structures, having anchors for fixing the blades at the rotor rim and relatively wide, hollow shanks arranged intermediate the said anchors and the bladesv proper,of primary cooling means, employing a plurality of gaseous currents re-circulated in closed cycles of movement through said hollow shanks and around the rim and web of the rotor,and secondary cooling means for re-cooling the respective gaseous currents in proportion to the amount of heat to be locally dissipated, the said primary cooling means comprising a plurality of cooling ribs, the front faces of which being opposed to said shanks and anchors of the blade structures, and to the rim and webof the rotor respectively, while their rear faces are opposed to the said secondary cooling means, the latter employing a liquid cooling agent, and comprising a plurality of ring shaped jackets, through which said liquid cooling

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US124407A 1936-07-01 1937-02-06 Gas turbine Expired - Lifetime US2141401A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE2141401X 1936-07-01
GB23413/38A GB508436A (en) 1938-08-08 1938-08-08 Improvements in or relating to gas turbines

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Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
US2479046A (en) * 1944-08-23 1949-08-16 United Aircraft Corp Limiting heat transfer to the turbine rotor
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
US2618461A (en) * 1948-10-05 1952-11-18 English Electric Co Ltd Gas turbine
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2628066A (en) * 1946-10-02 1953-02-10 Rolls Royce Turbine disk
US2656147A (en) * 1946-10-09 1953-10-20 English Electric Co Ltd Cooling of gas turbine rotors
US2684831A (en) * 1947-11-28 1954-07-27 Power Jets Res & Dev Ltd Turbine and like rotor
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
US2839268A (en) * 1950-01-18 1958-06-17 Allis Chalmers Mfg Co Gas turbine
US2915279A (en) * 1953-07-06 1959-12-01 Napier & Son Ltd Cooling of turbine blades
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2962259A (en) * 1956-02-03 1960-11-29 Napier & Son Ltd Turbine blade rings and methods of assembly
US2990156A (en) * 1956-08-17 1961-06-27 Gen Electric Blade damping means
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3269703A (en) * 1960-08-30 1966-08-30 Sundstrand Corp Gas turbine engine starter
US3738771A (en) * 1970-07-20 1973-06-12 Onera (Off Nat Aerospatiale) Rotor blades of rotary machines, provided with an internal cooling system
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement
CN102840144A (zh) * 2011-06-20 2012-12-26 通用电气公司 通风压缩机转子及配有所述转子的涡轮发动机
RU2553049C2 (ru) * 2011-07-01 2015-06-10 Альстом Текнолоджи Лтд Лопатка ротора турбины, ротор турбины и турбина

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
US2479046A (en) * 1944-08-23 1949-08-16 United Aircraft Corp Limiting heat transfer to the turbine rotor
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
US2628066A (en) * 1946-10-02 1953-02-10 Rolls Royce Turbine disk
US2656147A (en) * 1946-10-09 1953-10-20 English Electric Co Ltd Cooling of gas turbine rotors
US2684831A (en) * 1947-11-28 1954-07-27 Power Jets Res & Dev Ltd Turbine and like rotor
US2618461A (en) * 1948-10-05 1952-11-18 English Electric Co Ltd Gas turbine
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2722101A (en) * 1948-12-21 1955-11-01 Solar Aircraft Co Gas turbine sealing and cooling structure
US2839268A (en) * 1950-01-18 1958-06-17 Allis Chalmers Mfg Co Gas turbine
US2915279A (en) * 1953-07-06 1959-12-01 Napier & Son Ltd Cooling of turbine blades
US2962259A (en) * 1956-02-03 1960-11-29 Napier & Son Ltd Turbine blade rings and methods of assembly
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2990156A (en) * 1956-08-17 1961-06-27 Gen Electric Blade damping means
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3269703A (en) * 1960-08-30 1966-08-30 Sundstrand Corp Gas turbine engine starter
US3738771A (en) * 1970-07-20 1973-06-12 Onera (Off Nat Aerospatiale) Rotor blades of rotary machines, provided with an internal cooling system
US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement
CN102840144A (zh) * 2011-06-20 2012-12-26 通用电气公司 通风压缩机转子及配有所述转子的涡轮发动机
RU2553049C2 (ru) * 2011-07-01 2015-06-10 Альстом Текнолоджи Лтд Лопатка ротора турбины, ротор турбины и турбина
US9316105B2 (en) 2011-07-01 2016-04-19 Alstom Technology Ltd Turbine blade

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