US2743080A - Turbine rotors - Google Patents
Turbine rotors Download PDFInfo
- Publication number
- US2743080A US2743080A US158233A US15823350A US2743080A US 2743080 A US2743080 A US 2743080A US 158233 A US158233 A US 158233A US 15823350 A US15823350 A US 15823350A US 2743080 A US2743080 A US 2743080A
- Authority
- US
- United States
- Prior art keywords
- platforms
- blade
- blades
- turbine
- axial
- 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
Links
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
Definitions
- This invention relates to rotors of axial flow turbines having two or more stages, with especial reference to rotors for gas turbines.
- the turbine rotor blades are usually mounted in the rims of the turbine wheels by means of serrated roots, sometimes known as fir trees, and the invention makes use of this type of construction.
- the axial widths of they rims of mutually adjacent turbine wheels or discs are greater than the axial widths of the blades mounted in them so that the serrations at the roots of the blades do not occupy the whole axial length of the serrated slots in the rims of the wheels; and the gap between mutually adjacent wheel rims is filled by dummy platforms corresponding in number to the blades in each wheel and having serrated roots supported at each end in the parts of the serrated slots of the adjacent wheel rims unoccupied by the blade roots.
- the surfaces of these platforms may be shaped to an arc struck from the axis of the turbine shaft so that when assembled they form a complete ring flush with the blade platforms of the adjacent turbine wheels.
- the outer surfaces of the platice forms may be left fiat, in which case the complete ring pletely close, thus ensuring that the dummy platforms,
- a further object of the invention is the provision of adequate cooling of the opposed faces of mutually adjacent turbine wheels or discs, when the space between their rims is filled by a substantially continuous ring of dummy platforms.
- each of the dummyplatforms isv provided with a small slot or'notch .at or near one corner providing an opening between itand the nextdummy platform through which cooling air, fed into the space between the mutually adjacent turbine wheels for cooling the latter, can escape.
- the escaping air forms a layer of cooling air over the blade roots and blade platforms of the blade-row downstream of the ring of dummy platforms.
- the outer faces of the wheels carrying the first and last stages of blading are air-cooledin the usual way, the air escaping through the'clearance between the nozzle ring and the first row of moving blading and the clearance between the last row of moving blading and the exhaust cone; and the air escaping through the first of these clearances cools the platforms and inner ends of the blades of the firststage of rotorblading. Furthermore, the circulation of air through the spaces between mutually adjacent turbine wheels serves to cool the underfaces of the dummy platforms themselves.
- Figure l is an axial section of a two-stage axial flow turbine rotor
- Figure 2 is a broken plan view taken in the direction of arrow 2 of Figure l;
- FIG 3 is a section on the line 3--3 of Figure 1 of a blades 18.
- the blade roots 17 18 are of fir-tree form (see Figure 4) and each blade includes an integral platform 17 or 18
- the rims 10 and 11 of the discs 10, 11 are axially slotted at lb 11 ( Figure 2) to receive the fir-tree blade roots.
- Each disc has an equal number of blades and the blade roots 17 18 and the slots 10*, 11 are of the same fir-tree section, the slots 10, 11 being in mutual register circumferentially, i. e. so that when viewed endwise, each slot 10 exactly coincides with a slot 11.
- the two turbine discs 10, 11 are axially spaced at their peripheryby gaps corresponding approximately to the axial width of the blades.
- the blade-platforms 17 are substantially contiguous cireumferentially, and so are the blade-platforms 18 just suflicient clearance being allowed between them to allow for -expansion, so that the blade-platforms of each row of blades-presents a continuous annular drum-shaped surface.
- the axial gap between'thesesurfaces isfilled by a row ofdummy platforms 19 havingfir-tree roots 19 which are exactly similar tothose of the blades and are inserted into -the"open or unfilledends of'the slots 10, 11
- the dummy platforms 19 substantially fill the gap between'the bl'ade platforms 17 18 and-are substantially contiguous circumferentially, just sufiicient clearance both axially and circumferentially being provided to-allow for expansion.
- This method of constructing the part of the inner wall of the turbine annulus intermediate between mutually adjacent rows of blade-platforms avoids the imposition of additional thermal stresses on the discs, the elements comprising the intermediate part of the annulus-wall itself being also substantially free from thermal stressing.
- blade-supporting discs having axially enlarged hubs secured together and having rims axially spaced apart, a row of blades on each disc, each blade having a fir-trce root and a blade platform and the rims of the discs having axially extending fir-tree slots receiving the blade roots, the blade platforms of each row being substantially contiguous circumferentially and the platforms and roots of the bladesin each row being narrower axially than the axial width of thedisc rims and their fir-tree slots, and a row of dummy platforms having fir-tree roots, the ends of whichare supportedinthe fir-tree slots of mutually adjacent discs, the blade platforms and the dummy platforms being located entirelybeyond theouter peripheries of the disc rims, the dummy platforms being substantially contiguous circumferentially and substantially filling the axial gap between mutually adjacent rows of blade platforms so that the blade platforms and dummy platforms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB284189X | 1949-04-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2743080A true US2743080A (en) | 1956-04-24 |
Family
ID=10275321
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US158233A Expired - Lifetime US2743080A (en) | 1949-04-29 | 1950-04-26 | Turbine rotors |
Country Status (4)
Country | Link |
---|---|
US (1) | US2743080A (xx) |
CH (1) | CH284189A (xx) |
GB (1) | GB667194A (xx) |
NL (1) | NL72215C (xx) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3692429A (en) * | 1971-02-01 | 1972-09-19 | Westinghouse Electric Corp | Rotor structure and method of broaching the same |
US3745628A (en) * | 1971-07-29 | 1973-07-17 | Westinghouse Electric Corp | Rotor structure and method of construction |
US3894324A (en) * | 1971-08-14 | 1975-07-15 | Motoren Turbinen Union | Rotor for fluid flow machines |
US4277225A (en) * | 1977-09-23 | 1981-07-07 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Rotor for jet engines |
US5031400A (en) * | 1988-12-09 | 1991-07-16 | Allied-Signal Inc. | High temperature turbine engine structure |
US5350276A (en) * | 1992-04-17 | 1994-09-27 | Gec Alsthom Electromecanique Sa | High pressure modules of drum rotor turbines with admission of steam having very high characteristics |
EP2546461A1 (en) * | 2011-07-11 | 2013-01-16 | General Electric Company | Rotor assembly and corresponding gas turbine engine |
US20150023785A1 (en) * | 2013-07-19 | 2015-01-22 | Michael J. Stanko | Coupling for directly driven compressor |
CN107269316A (zh) * | 2017-08-17 | 2017-10-20 | 中南大学 | 一种燃气轮机中心拉杆式转子的锥形轮盘结构 |
US10385861B2 (en) * | 2012-10-03 | 2019-08-20 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
US10443603B2 (en) * | 2012-10-03 | 2019-10-15 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2901214A (en) * | 1954-04-12 | 1959-08-25 | Arthur J Slemmons | Turbine wheel and shaft assembly |
DE1044527B (de) * | 1955-07-16 | 1958-11-20 | Canadian Patents Dev | Vorrichtung zur Verbindung einer hohlen Turbinenwelle, insbesondere bei einem Gasturbinentriebwerk mit einem frei tragend angeordneten Turbinenlaufrad |
FR2295226A1 (fr) * | 1974-12-16 | 1976-07-16 | Europ Turb Vapeur | Dispositif de clavetage entre disques d'une turbine |
GB2293628B (en) * | 1994-09-27 | 1998-04-01 | Europ Gas Turbines Ltd | Turbines |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB319622A (en) * | 1928-09-24 | 1930-12-18 | Vladimir Kalabek | Gas turbine |
US2430185A (en) * | 1946-07-25 | 1947-11-04 | Continental Aviat & Engineerin | Turbine rotor |
GB599809A (en) * | 1945-01-15 | 1948-03-22 | Bristol Aeroplane Co Ltd | Improvements in axial flow compressors, turbines and the like |
GB612097A (en) * | 1946-10-09 | 1948-11-08 | English Electric Co Ltd | Improvements in and relating to the cooling of gas turbine rotors |
US2461402A (en) * | 1944-10-06 | 1949-02-08 | Power Jets Res & Dev Ltd | Rotor for multistage axial flow compressors and turbines |
US2497151A (en) * | 1946-03-04 | 1950-02-14 | Armstrong Siddeley Motors Ltd | Multidisk rotor |
-
0
- NL NL72215D patent/NL72215C/xx active
-
1949
- 1949-04-29 GB GB11456/49A patent/GB667194A/en not_active Expired
-
1950
- 1950-04-26 US US158233A patent/US2743080A/en not_active Expired - Lifetime
- 1950-04-28 CH CH284189D patent/CH284189A/de unknown
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB319622A (en) * | 1928-09-24 | 1930-12-18 | Vladimir Kalabek | Gas turbine |
US2461402A (en) * | 1944-10-06 | 1949-02-08 | Power Jets Res & Dev Ltd | Rotor for multistage axial flow compressors and turbines |
GB599809A (en) * | 1945-01-15 | 1948-03-22 | Bristol Aeroplane Co Ltd | Improvements in axial flow compressors, turbines and the like |
US2497151A (en) * | 1946-03-04 | 1950-02-14 | Armstrong Siddeley Motors Ltd | Multidisk rotor |
US2430185A (en) * | 1946-07-25 | 1947-11-04 | Continental Aviat & Engineerin | Turbine rotor |
GB612097A (en) * | 1946-10-09 | 1948-11-08 | English Electric Co Ltd | Improvements in and relating to the cooling of gas turbine rotors |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3692429A (en) * | 1971-02-01 | 1972-09-19 | Westinghouse Electric Corp | Rotor structure and method of broaching the same |
US3745628A (en) * | 1971-07-29 | 1973-07-17 | Westinghouse Electric Corp | Rotor structure and method of construction |
US3894324A (en) * | 1971-08-14 | 1975-07-15 | Motoren Turbinen Union | Rotor for fluid flow machines |
US4277225A (en) * | 1977-09-23 | 1981-07-07 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Rotor for jet engines |
US5031400A (en) * | 1988-12-09 | 1991-07-16 | Allied-Signal Inc. | High temperature turbine engine structure |
US5350276A (en) * | 1992-04-17 | 1994-09-27 | Gec Alsthom Electromecanique Sa | High pressure modules of drum rotor turbines with admission of steam having very high characteristics |
EP2546461A1 (en) * | 2011-07-11 | 2013-01-16 | General Electric Company | Rotor assembly and corresponding gas turbine engine |
US10385861B2 (en) * | 2012-10-03 | 2019-08-20 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
US10443603B2 (en) * | 2012-10-03 | 2019-10-15 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
US10519962B2 (en) | 2012-10-03 | 2019-12-31 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
US10533564B2 (en) | 2012-10-03 | 2020-01-14 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
US10533565B2 (en) | 2012-10-03 | 2020-01-14 | Praxair Technology, Inc. | Method for compressing an incoming feed air stream in a cryogenic air separation plant |
CN105378316A (zh) * | 2013-07-19 | 2016-03-02 | 普莱克斯技术有限公司 | 用于直接驱动的压缩机的联接件 |
US9371835B2 (en) * | 2013-07-19 | 2016-06-21 | Praxair Technology, Inc. | Coupling for directly driven compressor |
CN105378316B (zh) * | 2013-07-19 | 2019-03-01 | 普莱克斯技术有限公司 | 用于直接驱动的压缩机的联接件 |
US20150023785A1 (en) * | 2013-07-19 | 2015-01-22 | Michael J. Stanko | Coupling for directly driven compressor |
CN107269316A (zh) * | 2017-08-17 | 2017-10-20 | 中南大学 | 一种燃气轮机中心拉杆式转子的锥形轮盘结构 |
Also Published As
Publication number | Publication date |
---|---|
NL72215C (xx) | |
CH284189A (de) | 1952-07-15 |
GB667194A (en) | 1952-02-27 |
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