US2801822A - Mounting of blades in axial flow compressors, turbines, or the like - Google Patents

Mounting of blades in axial flow compressors, turbines, or the like Download PDF

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Publication number
US2801822A
US2801822A US200379A US20037950A US2801822A US 2801822 A US2801822 A US 2801822A US 200379 A US200379 A US 200379A US 20037950 A US20037950 A US 20037950A US 2801822 A US2801822 A US 2801822A
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United States
Prior art keywords
platforms
blades
axial flow
groove
casing
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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
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US200379A
Inventor
Speed Frank Leslie
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Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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
Priority claimed from GB135345A external-priority patent/GB600019A/en
Priority to GB135345A priority Critical patent/GB600019A/en
Priority claimed from GB3482845A external-priority patent/GB600057A/en
Priority to CH270334D priority patent/CH270334A/en
Priority to FR920037D priority patent/FR920037A/en
Priority claimed from US641316A external-priority patent/US2623728A/en
Priority to US641316A priority patent/US2623728A/en
Priority to NL126107A priority patent/NL70473C/xx
Priority to NL157174A priority patent/NL72629C/xx
Priority to US200379A priority patent/US2801822A/en
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Publication of US2801822A publication Critical patent/US2801822A/en
Application granted granted Critical
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to the mounting of the blades in the outer bladed structure of axial flow compressors, turbines and the like and while its application is not necessarily limited thereto it can be regarded as being concerned primarily with the mounting of fixed stator blading in axial flow multistage compressors, turbines, and ducted fans.
  • the blades should be mounted in a mechanically effective manner while being if possible individually removable. It is also desirable that they should be mounted in such a way that constructional considerations in relation to the machine as a whole are conveniently dealt with, notably the insertion and supporting of the blade in a casing. Further the blade mounting should preferably be such as to leave or provide as smooth and uninterrupted a surface as possible exposed to the fluid flow in the blade passages.
  • the present invention in its different aspects, seeks to provide for these various requirements and is intended to have immediate application to a multistage axial flow compressor to form part of a gas turbine power plant for aircraft propulsion although the invention is of course not limited to such application.
  • an outer bladed structure of an axial flow compressor turbine or the like comprising a circular section hollow blade supporting structure coaxial with the axis of rotation of the machine having on its radially inner surface at least one annularly directed groove alfording a non-retentive bladeseating, and a ring of radially inwardly extending blades or groups of blades having at their radially outer ends root platforms seating in said groove, of which ring of blades alternate blade platforms only are directly attached to the blade supporting structure, and these platforms have with the platforms of intervening blade platforms complementary interengagement whereby said intervening platforms are secured in the seating groove of the ring.
  • the ungrooved surface of the blade supporting structure is arranged to be in axial register with the exposed faces of the root platforms in the grooves so that the general profile of the fluid passages between the blades has a smooth continuous contour.
  • the blade platforms are of T shape in peripheral cross section, alternate platforms being inverted with respect to those adjacent to interlock thereunder, and the latter alone being directly attached to the supporting structure.
  • those platforms which are secured directly to the supporting structure are so secured by the provision of radially outwardly extending shanks thereon passing through the supporting structure and locked at an outer part thereof, while the tails of those Tplatforms which are secured directly to the supporting structure have a clearance from the floor of groove to ensure that when so secured they will clamp the cross members of the intermediate, inverted T-platforrns, in position against the floor of the groove.
  • Figure 1 is a part longitudinal section of a complete axial flow compressor having a stator construction in accordance with the invention
  • Figure 2 is a fragmentary peripheral transverse section of the compressor illustrated in Figure 1
  • Figures 3 and 4 are fragmentary axial sections of the compressor taken on the lines III--III and IV-IV respectively in Figure 2.
  • the compressor comprises a multistage bladed rotor 1 operating in an outer casing 2 consituting the main supporting structure for a number of rows of stator blades 3.
  • the latter are provided with integral shallow root platforms 4 suitably curved in the peripheral sense to suit the diameter at which they are placed, these platforms being seated in shallow grooves 5 formed in the inner face of the casing 2.
  • the blade platforms are made to correspond in depth with the shallow grooves so that the inner exposed surfaces of the platform and the ungrooved surface portions of the rings are in axial alignment to afford a general profile for the fluid passages between the blades having a smooth continuous contour.
  • each blade platform is of T-shape in transverse section taken on a plane normal to the axis of the casing 2, the tails 4c of alternate: platforms 4a extending into the groove 5 in which they are seated and having integral therewith the shanks 15 of securing bolts which pass through holes formed in the casing 2 and are held by nuts 16.
  • the intermediate T-shaped platforms dd are inverted with respect to the groove and their tails 4 are directed radially outwardly and their crossmembers or heads 42, which lie on the floor 5a of the groove 5, engage under the crossmembers or heads 41) of the bolted platforms 4m It is arranged that the tails 4c of the latter have a clearance from the floor of the groove to ensure that the crossmembers or heads 4e of the platforms 4d will be clamped in position in engagement with the floor 5a of the groove by the crossmernbers or heads 4b of the platforms 4a, this being the only means provided of anchoring the former in the groove.
  • the casing 2 is made in two halves 2a, 2b flanged at 20, 2d for bolting together as indicated in Figure 2 it being arranged that the last blades 3a in each half are blades which are bolted directly to the casing.
  • an outer bladed structure comprising a hollow tubular casing of circular cross-section, said casing being formed with a circumferentially extending groove in its radially inner surface; a circumferentially extending row of radially inwardly extending blades within said casing, each blade having at its radially outer end an individual root platform located in said groove; means securing circumferentially alternate platforms to said casing; and means retaining the intermediate platforms located between said alternate platforms against radially inward displacement, said means comprising complementary inter-engaging portions formed on said alternate and intermediate platforms, the portions on said alternate platforms overlapping in a radial sense and lying radially within the portions on the intermediate platforms.
  • an outer bladed structure comprising a hollow tubular casing of circular cross-section, said casing being formed with a circumferentially extending'groove in its radiallyinner surface; a circumferentially extending row of radially inwardly extending blades within said casing, each blade having at its radially outer end an individual root platform located in said groove; each platform being T-shaped in transverse cross section taken on a plane normal to the axisof the casing, and having a head extending circumferentially of the groove and a tail extending radially; circumferentially alternate platforms having the tails of the T directed radially outwardly, andeach intermediate platform located between the adjacent platforms having the tail of the T directed radially inwardly and the head of 15 the T seating on the floor of the groove and overlapping and engaging in a radial sense and lying radially outwardly of the heads of the Ts of the alternate platforms on each side thereof; and means securing said alternate

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

Description

'Aug. 6, 1957 F L SPEED 2,801,822
MOUNTING 0F BLADEs' IN AXIAL 110w COMFRESSORS TURBINES, OR THE LIKE Originaljiled Jan. 15, 1946 Fig. 2
M By
A Horn ey Uite Stats MOUNTING F BLADES IN AXIAL FLOW COM- PRESSORS, TURBINES, OR THE LIKE Frank Leslie Speed, Abingdon, England, assignor to Power Jets (Research and Development) Limited, London, England, a British company 2 Claims. (Cl. 253-48) This invention relates to the mounting of the blades in the outer bladed structure of axial flow compressors, turbines and the like and while its application is not necessarily limited thereto it can be regarded as being concerned primarily with the mounting of fixed stator blading in axial flow multistage compressors, turbines, and ducted fans. Where such compressors or like machines are required for high performance purposes in aircraft or similar circumstances, lightness is a desirable feature and it is of course also desirable that the blades should be mounted in a mechanically effective manner while being if possible individually removable. It is also desirable that they should be mounted in such a way that constructional considerations in relation to the machine as a whole are conveniently dealt with, notably the insertion and supporting of the blade in a casing. Further the blade mounting should preferably be such as to leave or provide as smooth and uninterrupted a surface as possible exposed to the fluid flow in the blade passages. The present invention, in its different aspects, seeks to provide for these various requirements and is intended to have immediate application to a multistage axial flow compressor to form part of a gas turbine power plant for aircraft propulsion although the invention is of course not limited to such application.
The present application is a division of application Serial No. 641,316, in the name of Feilden, filed January 15, 1946, now Patent No. 2,623,728.
According to this invention there is provided an outer bladed structure of an axial flow compressor turbine or the like, comprising a circular section hollow blade supporting structure coaxial with the axis of rotation of the machine having on its radially inner surface at least one annularly directed groove alfording a non-retentive bladeseating, and a ring of radially inwardly extending blades or groups of blades having at their radially outer ends root platforms seating in said groove, of which ring of blades alternate blade platforms only are directly attached to the blade supporting structure, and these platforms have with the platforms of intervening blade platforms complementary interengagement whereby said intervening platforms are secured in the seating groove of the ring. Preferably the ungrooved surface of the blade supporting structure is arranged to be in axial register with the exposed faces of the root platforms in the grooves so that the general profile of the fluid passages between the blades has a smooth continuous contour.
In one practical form of the invention, the blade platforms are of T shape in peripheral cross section, alternate platforms being inverted with respect to those adjacent to interlock thereunder, and the latter alone being directly attached to the supporting structure. Preferably in such a case those platforms which are secured directly to the supporting structure are so secured by the provision of radially outwardly extending shanks thereon passing through the supporting structure and locked at an outer part thereof, while the tails of those Tplatforms which are secured directly to the supporting structure have a clearance from the floor of groove to ensure that when so secured they will clamp the cross members of the intermediate, inverted T-platforrns, in position against the floor of the groove.
Further and more detailed features of the invention will appear from the following description with reference to the example of construction illustrated in the accompanying drawings, in which:
Figure 1 is a part longitudinal section of a complete axial flow compressor having a stator construction in accordance with the invention; and Figure 2 is a fragmentary peripheral transverse section of the compressor illustrated in Figure 1; and Figures 3 and 4 are fragmentary axial sections of the compressor taken on the lines III--III and IV-IV respectively in Figure 2.
In the construction illustrated, the compressor comprises a multistage bladed rotor 1 operating in an outer casing 2 consituting the main supporting structure for a number of rows of stator blades 3. The latter are provided with integral shallow root platforms 4 suitably curved in the peripheral sense to suit the diameter at which they are placed, these platforms being seated in shallow grooves 5 formed in the inner face of the casing 2.
It will be noted that the blade platforms are made to correspond in depth with the shallow grooves so that the inner exposed surfaces of the platform and the ungrooved surface portions of the rings are in axial alignment to afford a general profile for the fluid passages between the blades having a smooth continuous contour.
As will be seen from Figures 24 only circumferentially alternate blades are directly secured in the platform receiving grooves. Each blade platform is of T-shape in transverse section taken on a plane normal to the axis of the casing 2, the tails 4c of alternate: platforms 4a extending into the groove 5 in which they are seated and having integral therewith the shanks 15 of securing bolts which pass through holes formed in the casing 2 and are held by nuts 16. The intermediate T-shaped platforms dd are inverted with respect to the groove and their tails 4 are directed radially outwardly and their crossmembers or heads 42, which lie on the floor 5a of the groove 5, engage under the crossmembers or heads 41) of the bolted platforms 4m It is arranged that the tails 4c of the latter have a clearance from the floor of the groove to ensure that the crossmembers or heads 4e of the platforms 4d will be clamped in position in engagement with the floor 5a of the groove by the crossmernbers or heads 4b of the platforms 4a, this being the only means provided of anchoring the former in the groove.
In order to facilitate assembly of the parts, the casing 2 is made in two halves 2a, 2b flanged at 20, 2d for bolting together as indicated in Figure 2 it being arranged that the last blades 3a in each half are blades which are bolted directly to the casing.
I claim:
1. In an axial flow bladed rotary device, an outer bladed structure comprising a hollow tubular casing of circular cross-section, said casing being formed with a circumferentially extending groove in its radially inner surface; a circumferentially extending row of radially inwardly extending blades within said casing, each blade having at its radially outer end an individual root platform located in said groove; means securing circumferentially alternate platforms to said casing; and means retaining the intermediate platforms located between said alternate platforms against radially inward displacement, said means comprising complementary inter-engaging portions formed on said alternate and intermediate platforms, the portions on said alternate platforms overlapping in a radial sense and lying radially within the portions on the intermediate platforms.
2. In an axial flow bladed rotary device, an outer bladed structure comprising a hollow tubular casing of circular cross-section, said casing being formed with a circumferentially extending'groove in its radiallyinner surface; a circumferentially extending row of radially inwardly extending blades within said casing, each blade having at its radially outer end an individual root platform located in said groove; each platform being T-shaped in transverse cross section taken on a plane normal to the axisof the casing, and having a head extending circumferentially of the groove and a tail extending radially; circumferentially alternate platforms having the tails of the T directed radially outwardly, andeach intermediate platform located between the adjacent platforms having the tail of the T directed radially inwardly and the head of 15 the T seating on the floor of the groove and overlapping and engaging in a radial sense and lying radially outwardly of the heads of the Ts of the alternate platforms on each side thereof; and means securing said alternate blades to 5 the casing.
References Cited in the file of this patent UNITED STATES PATENTS 747,857 Curtis Dec. 22, 1903 775,108 Elliott Nov. 15, 1904 779,911 Curtis Jan. 10, 1905 890,635 FOX June 16, 1908 2,316,813 Schaper Apr. 20, 1943 2,510,606 Price June 6, 1950
US200379A 1945-01-16 1950-12-12 Mounting of blades in axial flow compressors, turbines, or the like Expired - Lifetime US2801822A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
GB135345A GB600019A (en) 1945-12-21 1945-01-16 Improvements in or relating to the mounting of blades in compressors, turbines and the like
CH270334D CH270334A (en) 1945-01-16 1946-01-08 Blade carrier in axial centrifugal machines.
FR920037D FR920037A (en) 1945-01-16 1946-01-14 Improvements made to paddle-wheel machines such as turbine compressors or similar
US641316A US2623728A (en) 1945-01-16 1946-01-15 Mounting of blades in compressors, turbines, and the like
NL126107A NL70473C (en) 1945-01-16 1946-06-24
NL157174A NL72629C (en) 1945-01-16 1950-11-08
US200379A US2801822A (en) 1945-01-16 1950-12-12 Mounting of blades in axial flow compressors, turbines, or the like

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB135345A GB600019A (en) 1945-12-21 1945-01-16 Improvements in or relating to the mounting of blades in compressors, turbines and the like
GB3482845A GB600057A (en) 1945-12-21 Improvements in or relating to the mounting of blades in axial flow compressors, turbines, or the like
US641316A US2623728A (en) 1945-01-16 1946-01-15 Mounting of blades in compressors, turbines, and the like
US200379A US2801822A (en) 1945-01-16 1950-12-12 Mounting of blades in axial flow compressors, turbines, or the like

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US2801822A true US2801822A (en) 1957-08-06

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US200379A Expired - Lifetime US2801822A (en) 1945-01-16 1950-12-12 Mounting of blades in axial flow compressors, turbines, or the like

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US (1) US2801822A (en)
CH (1) CH270334A (en)
FR (1) FR920037A (en)
NL (2) NL70473C (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3112916A (en) * 1962-04-30 1963-12-03 Gen Electric Fluid flow machine assembly
US4245954A (en) * 1978-12-01 1981-01-20 Westinghouse Electric Corp. Ceramic turbine stator vane and shroud support
US5211537A (en) * 1992-03-02 1993-05-18 United Technologies Corporation Compressor vane lock
US20050132707A1 (en) * 2001-11-20 2005-06-23 Andreas Gebhardt Gas turbo set
US20060045745A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Vane attachment arrangement
US20090053056A1 (en) * 2007-08-24 2009-02-26 Siemens Power Generation, Inc. Turbine Vane Securing Mechanism
US20100196149A1 (en) * 2008-12-12 2010-08-05 United Technologies Corporation Apparatus and Method for Preventing Cracking of Turbine Engine Cases
US20140147265A1 (en) * 2012-11-29 2014-05-29 Techspace Aero S.A. Axial Turbomachine Blade with Platforms Having an Angular Profile
US20150010395A1 (en) * 2013-07-03 2015-01-08 Techspace Aero S.A. Stator Blade Sector for an Axial Turbomachine with a Dual Means of Fixing

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1045591B (en) * 1951-02-27 1958-12-04 United Aircraft Corp Guide vane arrangement for multi-stage axial compressors
BE543709A (en) * 1954-12-16

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US747857A (en) * 1902-08-01 1903-12-22 Charles G Curtis Elastic-fluid turbine.
US775108A (en) * 1904-05-26 1904-11-15 William S Elliott Elastic-fluid turbine.
US779911A (en) * 1902-08-01 1905-01-10 Charles G Curtis Elastic-fluid turbine.
US890635A (en) * 1906-02-14 1908-06-16 Gen Electric Elastic-fluid turbine.
US2316813A (en) * 1939-07-22 1943-04-20 Holzwarth Gas Turbine Co Bearer for the stationary vanes of rotary motors
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US747857A (en) * 1902-08-01 1903-12-22 Charles G Curtis Elastic-fluid turbine.
US779911A (en) * 1902-08-01 1905-01-10 Charles G Curtis Elastic-fluid turbine.
US775108A (en) * 1904-05-26 1904-11-15 William S Elliott Elastic-fluid turbine.
US890635A (en) * 1906-02-14 1908-06-16 Gen Electric Elastic-fluid turbine.
US2316813A (en) * 1939-07-22 1943-04-20 Holzwarth Gas Turbine Co Bearer for the stationary vanes of rotary motors
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3112916A (en) * 1962-04-30 1963-12-03 Gen Electric Fluid flow machine assembly
US4245954A (en) * 1978-12-01 1981-01-20 Westinghouse Electric Corp. Ceramic turbine stator vane and shroud support
US5211537A (en) * 1992-03-02 1993-05-18 United Technologies Corporation Compressor vane lock
US7013652B2 (en) * 2001-11-20 2006-03-21 Alstom Technology Ltd Gas turbo set
US20050132707A1 (en) * 2001-11-20 2005-06-23 Andreas Gebhardt Gas turbo set
US7238003B2 (en) 2004-08-24 2007-07-03 Pratt & Whitney Canada Corp. Vane attachment arrangement
US20060045745A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Vane attachment arrangement
US20090053056A1 (en) * 2007-08-24 2009-02-26 Siemens Power Generation, Inc. Turbine Vane Securing Mechanism
US7862296B2 (en) 2007-08-24 2011-01-04 Siemens Energy, Inc. Turbine vane securing mechanism
US20100196149A1 (en) * 2008-12-12 2010-08-05 United Technologies Corporation Apparatus and Method for Preventing Cracking of Turbine Engine Cases
US8662819B2 (en) * 2008-12-12 2014-03-04 United Technologies Corporation Apparatus and method for preventing cracking of turbine engine cases
US20140147265A1 (en) * 2012-11-29 2014-05-29 Techspace Aero S.A. Axial Turbomachine Blade with Platforms Having an Angular Profile
US10202859B2 (en) * 2012-11-29 2019-02-12 Safran Aero Boosters Sa Axial turbomachine blade with platforms having an angular profile
US20150010395A1 (en) * 2013-07-03 2015-01-08 Techspace Aero S.A. Stator Blade Sector for an Axial Turbomachine with a Dual Means of Fixing
US9951654B2 (en) * 2013-07-03 2018-04-24 Safran Aero Boosters Sa Stator blade sector for an axial turbomachine with a dual means of fixing

Also Published As

Publication number Publication date
FR920037A (en) 1947-03-25
CH270334A (en) 1950-08-31
NL70473C (en) 1952-07-16
NL72629C (en) 1953-05-16

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