US3582230A - Turbomachine with cooled rotor - Google Patents

Turbomachine with cooled rotor Download PDF

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Publication number
US3582230A
US3582230A US819771A US3582230DA US3582230A US 3582230 A US3582230 A US 3582230A US 819771 A US819771 A US 819771A US 3582230D A US3582230D A US 3582230DA US 3582230 A US3582230 A US 3582230A
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US
United States
Prior art keywords
rotor
ducts
feed
section
housing
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.)
Expired - Lifetime
Application number
US819771A
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English (en)
Inventor
David Schmidt
Paul Moser
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.)
Brown Boveri Sulzer Turbomaschinen AG
Original Assignee
Brown Boveri Sulzer Turbomaschinen AG
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
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Application filed by Brown Boveri Sulzer Turbomaschinen AG filed Critical Brown Boveri Sulzer Turbomaschinen AG
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Publication of US3582230A publication Critical patent/US3582230A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • 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

Definitions

  • a turbomachine for an elastic fluid having a rotor cooled by an elastic fluid which in the region of the roots of the rotor blades comprises cooling ducts, and a supply duct to supply coolant to said cooling ducts, which is formed by a section of the rotor shaft situated at the high pressure side of the blading and by a part of the housing.
  • a number of feed ducts corresponding to the number of said cooling ducts, is provided, said feed ducts being connected to said cooling ducts and having a cross section by a multiple greater than that of said cooling ducts, the inlet-side mouths of said feed ducts being situated in the region of the outlet-side mouth of said supply duct.
  • the cooling ducts must be kept small in cross section for strength reasons in the region of the blade roots.
  • the coolant is supplied to the cooling ducts through an annular supply duct bounded by the rotor shaft and a housing part.
  • the coolant has approximately half the peripheral speed of the rotor shaft and, therefore, has an inclined direction of arrival flow relatively to the cooling ducts. This causes a considerable throttling effect, which can limit to an undesirable or intolerable extent the quantity of coolant flowing through the cooling ducts.
  • the same difficulty occurs to an even greater extent in the known installations wherein the coolant is supplied through stationary nozzles.
  • aturbomachine of the type described initially is so constructed according to the invention that a section of the rotor, hub situated at the high pressure side of the first ring of rotor blades, as viewed in the direction of the pressure gradient, comprises a number of feed ducts corresponding to the number of cooling ducts, the said feed ducts being connected thereto and being arranged substantially parallel to the rotor axis, and their cross section being greater by a multiple than that of the cooling ducts at least along a section at the high pressure side, and their inlet-side mouths being situated in the region of the outlet-side mouth of the supply duct.
  • FIG. I shows a fragmentary axial sectional view through a gas turbine
  • FIG. 2a shows a fragmentary view in section taken at right angles to the axis through the rotor of the turbine on the line 20-20 of FIG. 1.
  • FIG. 2b shows a fragmentary section similar to FIG. 2a, but taken on the line 2b-2b of FIG. 1.
  • FIG. 3 shows a fragmentary view from a development on the section taken on the line 3-3 in FIG. I.
  • the illustrated gas turbine comprises a housing 1 having guide blades 2, of which two rings of guide blades are visible, and also a rotor 3 having rotor blades 4, two rings of rotor blades being visible.
  • the arrow 5 shows the direction of the pressure gradient and at the same time the direction of flow of the driving medium.
  • the first ring of rotor blades, or the blades thereof, as viewed in the direction of the pressure gradient, are designated as 4.
  • cooling ducts 7 7 which are parallel to the rotor axis.
  • a supply duct 8 serving to supply coolant to the ring of rotor blades 4 is surrounded by a housing part 10 and by a section 9 of the rotor shaft situated at the high pressure side and at the same time the inlet-side of the blading 2, 4 and is constructed as an annular gap.
  • the rotor 3 can be mounted for example at the inletside outside the turbine in a compressor for the driving medium, the said compressor being assembled with the said turbine, cool-driving medium flowing between the shaft and the housing from the compressor to the first ring of rotor blades of the turbine.
  • a section 11 of the rotor hub 12 situated at the high pressure side of the first ring of rotor blades 4, as viewed in the direction 5 of the pressure gradient, comprises a number of feed ducts 13 corresponding to the number of cooling ducts 7, the said feed ducts being connected to the said cooling ducts and being arranged parallel to the rotor axis, and their cross section being for example five times greater than that of the cooling ducts 7 along a section at the high pressure side corresponding to approximately half of their axial extent, the inlet-side mouths 14 0f the said feed ducts being situated in the region of the outlet-side mouth 15 of the supply duct 8.
  • the inlet-side mouths 16 of the cooling ducts 7 on the one hand and the outlet-side mouth 15 of the supply duct 8 on the other hand have radial spacing from one another.
  • the radial extent of the feed ducts 13 along the section thereof at the high pressure side corresponds to the aforesaid radial spacing.
  • the increase in the cross section of the feed ducts 13 relatively to that of the cooling ducts 7 is obtained exclusively by the greater extent of the feed ducts in the radial direction. This kind of construction achieves a satisfactory use of the space available.
  • the cooling ducts 7 are arranged radially inwardly of the blade roots 6 and adjoining the latter.
  • the feed ducts 13 extend from the radial region of the radially inner surfaces of the blade roots 6 radially inwardly.
  • the section 11 of the rotor hub 12 which is provided with the feed ducts 13 comprises grooves 19 which are in alignment with the axial grooves 17, receiving the blade roots 6, of the first rotor disc 18, as viewed in the direction 5 of the pressure gradient, the said grooves receiving feet 20 of cover segments 21.
  • the feed ducts 13 are. arranged radially inwardly of these feet 20 and adjoining the latter. This kind of construction has the advantage that the grooves 19 can be machined together with the grooves 17 in a single working operation. Since the section 11 of the rotor hub is subdivided at the periphery by the grooves 13, 19, dangerous temperature stresses at this region are obviated.
  • the first rotor disc 18 has a larger radius than the section 11 of the rotor hub 12 which is provided with the feed ducts 13.
  • a ring 22 is provided which surrounds this section 11 of the rotor hub 12 and is connected at the high pressure side to the housing 1 and whose low-pressure outer edge 23 is in axial alignment with the high-pressure outer edge 24 of the first rotor disc 18, and whose outer generated surface forms an axial section of the inner boundary surface of the working medium duct 25.
  • the inner generated surface of the ring 22 bounds together with the generated surface of the aforesaid section 11 of the rotor hub 12, or with the outer surfaces of the cover segments 21, an annular sealing gap 26 which has sealing labyrinths.
  • the ring 22 described hereinbefore affords the advantage that for sealing the coolant-conducting passage 8, I3 relatively to the working medium passage 25 a sealing gap 26 of considerable axial extent is obtained which gives an adequate sealing effect even with the tolerances necessary in view of the different thermal expansion of the rotor and housing. Since the cover segments 21 are subjected to less considerable forces than the rotor blades 4, the feet 20 can be shorter and comprise fewer teeth than the blade roots 6.
  • the arrow 27 indicates the direction of rotation of the rotor 3.
  • the edges between the wall surfaces 28 of the feed ducts directed oppositely to the direction of rotation 27 and the high-pressure end wall 29 of the rotor hub 12 are rounded-off; they could also be bevelled. This measure serves to improve the inflow conditions in the coolant entering the feed ducts.
  • the measures according to the invention are not limited to a gas turbine but may also be used in the case of steam turbines and turbocompressors.
  • An axial flc-w turbomachine for an elastic fluid of the type including a housing (1); a plurality of axially spaced, coaxial, circular series of guide blades (2) carried by and extending inward from said housing; a rotor (3) mounted for rotation in said housing; a plurality of axially spaced, coaxial, circular series of rotor blades (4 ,4 (25) defined between the housing and the rotor and into which said blades project, recesses formed in said rotor and arranged to receive and confine therein the root portions of corresponding rotor blades, the improvement which comprises means to supply coolant to the region of the roots of the rotor blades of at least the series of rotor blades nearest the high pressure end of the machine and comprising a three part flow path extending in the direction of the pressure gradient through the machine, the three parts being respectively an annular inlet section (8) defined between a portion of the housing and the rotor, and extending inward from the high pressure end of the housing, an intermediate section including
  • said rotor includes axial grooves 17 formed therein, each groove receiving the root portion of a rotor blade, said cooling ducts being formed in said grooves beneath the root portion therein; said feed ducts comprising axial feed grooves formed in said rotor in alignment with the blade root portion-receiving grooves and cover segments having projecting feet received in said feed ducts to hold said cover segments in place and enclose said feed ducts.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US819771A 1969-02-26 1969-04-28 Turbomachine with cooled rotor Expired - Lifetime US3582230A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH285569A CH495496A (de) 1969-02-26 1969-02-26 Turbomaschine mit gekühltem Rotor

Publications (1)

Publication Number Publication Date
US3582230A true US3582230A (en) 1971-06-01

Family

ID=4243087

Family Applications (1)

Application Number Title Priority Date Filing Date
US819771A Expired - Lifetime US3582230A (en) 1969-02-26 1969-04-28 Turbomachine with cooled rotor

Country Status (5)

Country Link
US (1) US3582230A (enrdf_load_stackoverflow)
CH (1) CH495496A (enrdf_load_stackoverflow)
DE (1) DE2004761A1 (enrdf_load_stackoverflow)
GB (1) GB1305431A (enrdf_load_stackoverflow)
NL (1) NL6910908A (enrdf_load_stackoverflow)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4648791A (en) * 1984-06-30 1987-03-10 Bbc Brown, Boveri & Company, Limited Rotor, consisting essentially of a disc requiring cooling and of a drum
EP1041246A1 (de) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
US20030097841A1 (en) * 2000-05-05 2003-05-29 Hans-Joachim Endries Method and device for cooling the inflow area of the shaft of a steam turbine
US20100162564A1 (en) * 2008-11-19 2010-07-01 Alstom Technology Ltd Method for machining a gas turbine rotor
CN110030045A (zh) * 2018-01-12 2019-07-19 通用电气公司 具有环形腔的涡轮发动机

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3310396A1 (de) * 1983-03-18 1984-09-20 Kraftwerk Union AG, 4330 Mülheim Md-dampfturbine in einflutiger bauweise fuer eine hochtemperaturdampfturbinenanlage mit zwischenueberhitzung
CA1209482A (en) * 1983-12-22 1986-08-12 Douglas L. Kisling Two stage rotor assembly with improved coolant flow
EP0353447A1 (en) * 1988-07-29 1990-02-07 Westinghouse Electric Corporation Side-entry grooves for mounting turbine blades
EP0894941B1 (de) * 1997-07-28 2003-03-12 ALSTOM (Switzerland) Ltd Rotor einer Strömungsmaschine
EP0926311B1 (de) * 1997-12-24 2003-07-09 ALSTOM (Switzerland) Ltd Rotor einer Strömungsmaschine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
US2988325A (en) * 1957-07-18 1961-06-13 Rolls Royce Rotary fluid machine with means supplying fluid to rotor blade passages
US3343806A (en) * 1965-05-27 1967-09-26 Gen Electric Rotor assembly for gas turbine engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
US2988325A (en) * 1957-07-18 1961-06-13 Rolls Royce Rotary fluid machine with means supplying fluid to rotor blade passages
US3343806A (en) * 1965-05-27 1967-09-26 Gen Electric Rotor assembly for gas turbine engines

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4648791A (en) * 1984-06-30 1987-03-10 Bbc Brown, Boveri & Company, Limited Rotor, consisting essentially of a disc requiring cooling and of a drum
EP1041246A1 (de) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
WO2000058606A1 (de) * 1999-03-29 2000-10-05 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene gasturbinenschaufel sowie vorrichtung und verfahren zur herstellung eines verteilerraums der gasturbinenschaufel
JP2002540347A (ja) * 1999-03-29 2002-11-26 シーメンス アクチエンゲゼルシヤフト 冷却材の貫流する鋳造ガスタービン翼並びにガスタービン翼の分配室の製造装置及び方法
US6565318B1 (en) 1999-03-29 2003-05-20 Siemens Aktiengesellschaft Cast gas turbine blade through which coolant flows, together with appliance and method for manufacturing a distribution space of the gas turbine blade
US20030097841A1 (en) * 2000-05-05 2003-05-29 Hans-Joachim Endries Method and device for cooling the inflow area of the shaft of a steam turbine
US6824351B2 (en) * 2000-05-05 2004-11-30 Siemens Aktienegesellschaft Method and device for cooling the inflow area of the shaft of a steam turbine
US20100162564A1 (en) * 2008-11-19 2010-07-01 Alstom Technology Ltd Method for machining a gas turbine rotor
US8281486B2 (en) * 2008-11-19 2012-10-09 Alstom Technology Ltd. Method for machining a gas turbine rotor
CN110030045A (zh) * 2018-01-12 2019-07-19 通用电气公司 具有环形腔的涡轮发动机
CN110030045B (zh) * 2018-01-12 2022-08-16 通用电气公司 具有环形腔的涡轮发动机

Also Published As

Publication number Publication date
NL6910908A (enrdf_load_stackoverflow) 1970-08-28
GB1305431A (enrdf_load_stackoverflow) 1973-01-31
CH495496A (de) 1970-08-31
DE2004761A1 (de) 1970-09-10

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