US3339833A - Axial fluid flow machine such as a compressor or turbine - Google Patents

Axial fluid flow machine such as a compressor or turbine Download PDF

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Publication number
US3339833A
US3339833A US441143A US44114365A US3339833A US 3339833 A US3339833 A US 3339833A US 441143 A US441143 A US 441143A US 44114365 A US44114365 A US 44114365A US 3339833 A US3339833 A US 3339833A
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United States
Prior art keywords
blades
dove
fluid flow
compressor
mounting member
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Expired - Lifetime
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US441143A
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Bill Arthur
Steel Thomas
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Rolls Royce PLC
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Rolls Royce PLC
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Priority claimed from GB4800463A external-priority patent/GB991357A/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to US441143A priority Critical patent/US3339833A/en
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Publication of US3339833A publication Critical patent/US3339833A/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
    • 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

Definitions

  • AXIAL FLUID FLOW MACHINE SUCH AS A COMPRESSOR OR TURBINE Filed March 19, 1965 2 Sheets-Sheet 1 A. BILL ETAL Sept. 5, 1967
  • AXIAL FLUID FLOW MACHINE SUCH AS A COMPRESSOR OR TURBINE Filed March 19, 1965 2 Sheets-Sheet Z1 United States Patent 3,339,833
  • AXIAL FLUID FLOW MACHINE SUCH AS A COMPRESSOR 0R TURBINE Arthur Bill and Thomas Steel, Derby, England, assignors to Rolls-Royce Limited, Derby, England, a company of Great Britain Filed Mar. 19, 1965, Ser. No. 441,143 6 Claims. (Cl. 230-133)
  • This invention concerns axial fluid flow machines such as axial flow compressors, turbines, fans and propellers, and machines provided therewith e.g. gas turbine engines.
  • an axial fluid flow machine comprising blades having root portions by which they are attached to a mounting member, the root portions of said blades being of dove-tail shape and being disposed within and extending radially through corresponding dove-tail slots in said mounting member such that the root portions project radially from a surface of said mounting member remote from the working positions of said blades, the projecting root portions of said blades being bonded to the said surface of said mounting member.
  • the term blade used herein is intended to include vanes.
  • the root portions project from said surface of the mounting member for a major portion of their axial length.
  • the mounting member may be generally U-shaped in cross-section, the said root portions projecting through the base of said U-shaped mounting member.
  • the vanes or blades may be rotor blades, the mounting member being a rotor disc.
  • the vanes or blades may be stator vanes or blades, the mounting member forming part of the casing of said machine.
  • stator vanes or blades may also be bonded to an internal member, said internal member providing support for a rotor bearing of said machine.
  • the vanes or blades may be of metal or may be formed of fibre reinforced synthetic resin material.
  • the mounting member is also formed of fibre reinforced synthetic resin material, an adhesive being used to bond together the vanes or blades and said mounting member.
  • the vanes or blades may be compressor blades, the machine being an axial flow compressor.
  • the invention also includes a gas turbine engine provided with a compressor as set forth above.
  • FIGURE 1 is a cut-away view of a gas turbine engine in accordance with the present invention
  • FIGURE 2 is a part sectional view of part of the engine of FIGURE 1, taken in line 2-2 of that figure,
  • FIGURE 3 is a part sectional view of part of the components shown in FIGURE 2 taken in line 3--3 of that figure, and
  • FIGURE 4 is a general view of the components shown in FIGURES 2 and 3.
  • a gas turbine engine includes a compressor 11 comprising rows of rotor blades 12, 13, 14, 15, rows of stator vanes 16, 17 and 18 and external casing 20.
  • Rotor blades 12 and 13 are mounted on rotor discs 21, 22, attached to a rotor shaft 23.
  • Rotor blades 14, 15 are mounted on rotor discs 24, 25 attached to rotor shaft 26.
  • Stator vanes 16 are disposed between the rows of rotor blades 12 and 13 and are connected to an external annular casing member 30, which forms part of the casing 20 of the compressor, and to an internal annular member 31.
  • the annular member 31 is connected to a bearing 32 within which shaft 23 is journalled.
  • the row of stator vanes 16 supports the bearing 32 and the rotor shaft 23.
  • casing member 30 is substantially U-shaped in cross-section, having side walls 33, 34 and a base 35.
  • An annular boss 36 is disposed between side walls 33, 34, on the external surface 37 of base 35.
  • Casing member 30 is provided with a plurality of axially extending, angularly spaced apart, dove-tail slots 38 within which are disposed corresponding dove-tail roots 40 of stator vanes 16.
  • the roots 40 are somewhat larger, in radial dimension, than the base 35, they therefore project above the external surface 37.
  • the roots 40 project above surface 37 for a major portion of their axial length and they define, with external surface 37, two angled portions 41, 42 in which bonding material (not shown) is disposed to bond the roots 40 to external surface 37.
  • the stator vanes 16 are A fastened to the external casing member 30 by their dovetail joints and by bonding material.
  • the compressor 11 may be formed of metal e.g. a light alloy, in which case the roots 40 may be bonded, brazed or welded to the external surface 37.
  • the compressor 11 may be formed of fibre reinforced synthetic resin material, in which case the roots 40 are bonded to external surface 37 by an adhesive or by further fibre reinforced synthetic resin material fused to both the roots 40 and the external surface 37.
  • the bonding process may be performed after the vanes have been assembled.
  • the bonding process is also relatively easy, since the surfaces to be bonded are readily accessible.
  • the internal annular member 31 is also substantially U-shaped in cross-section, having spaced radial flanges 50, 51 and a base 52.
  • the annular member 31 is provided with a plurality of axially extending, angularly spaced apart dove-tail slots 54 within which dove-tail root portions 55 of vanes 16 are disposed.
  • the root portions 55 also extend through the base 52 and project above the surface 56 of annular member 31, as described above with reference to roots 40 and member 30.
  • root portions 55 are bonded to the surface 56 by adhesive or by brazing or welding, for example, and by their dove-tail connections.
  • stator vanes 16 are attached to their supporting members by the particular dove-tail connections described above, it will be appreciated that any stator vane or rotor blade may be so connected to its supporting member.
  • stator vanes 17 and 18 may be connected to the casing 20 in this manner and rotor blades 12, 13, 14 and 15 may be connected to rotor discs 21, 22, 24, 25 respectively, in a similar manner.
  • the same method of connecting blades to their supporting member may be used for any axial fluid fiow machine which uses bladed rotors and stators e.g. turbines, fans and propellers.
  • An axial fluid flow machine comprising concentric inner and outer annular mounting members, angularly spaced apart dove-tail slots in each said mounting member, the slotsin one mounting member being inclined and oppositely disposed from the outer and inner sides of the support members with respect to the slots in the other mounting member, a plurality of radially disposed blades extending between said members, each blade having a working portion and having a root portion at each end thereof, the root portions of each blade being of dove-tail shape and being disposed within and extending radially through said dove-tail slots to lock and support the blades against movement radially and axially, said root portions projecting radially from the surfaces of said mounting members remote from the working portion of each blade,
  • annular mounting members are formed of fibre-reinforced synthetic resin material and the projecting root portions of said blades are bonded to the said surfaces of the mounting members by adhesive.

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

Description

Sept. 5, 1967 A. BILL ETAL 3,339,833
AXIAL FLUID FLOW MACHINE SUCH AS A COMPRESSOR OR TURBINE Filed March 19, 1965 2 Sheets-Sheet 1 A. BILL ETAL Sept. 5, 1967 AXIAL FLUID FLOW MACHINE SUCH AS A COMPRESSOR OR TURBINE Filed March 19, 1965 2 Sheets-Sheet Z1 United States Patent 3,339,833 AXIAL FLUID FLOW MACHINE SUCH AS A COMPRESSOR 0R TURBINE Arthur Bill and Thomas Steel, Derby, England, assignors to Rolls-Royce Limited, Derby, England, a company of Great Britain Filed Mar. 19, 1965, Ser. No. 441,143 6 Claims. (Cl. 230-133) This invention concerns axial fluid flow machines such as axial flow compressors, turbines, fans and propellers, and machines provided therewith e.g. gas turbine engines.
According to the present invention there is provided an axial fluid flow machine comprising blades having root portions by which they are attached to a mounting member, the root portions of said blades being of dove-tail shape and being disposed within and extending radially through corresponding dove-tail slots in said mounting member such that the root portions project radially from a surface of said mounting member remote from the working positions of said blades, the projecting root portions of said blades being bonded to the said surface of said mounting member. The term blade used herein is intended to include vanes.
In a preferred embodiment, the root portions project from said surface of the mounting member for a major portion of their axial length.
The mounting member may be generally U-shaped in cross-section, the said root portions projecting through the base of said U-shaped mounting member.
The vanes or blades may be rotor blades, the mounting member being a rotor disc. Alternatively, the vanes or blades may be stator vanes or blades, the mounting member forming part of the casing of said machine.
The stator vanes or blades may also be bonded to an internal member, said internal member providing support for a rotor bearing of said machine.
The vanes or blades may be of metal or may be formed of fibre reinforced synthetic resin material. In a preferred embodiment the mounting member is also formed of fibre reinforced synthetic resin material, an adhesive being used to bond together the vanes or blades and said mounting member.
The vanes or blades may be compressor blades, the machine being an axial flow compressor.
The invention also includes a gas turbine engine provided with a compressor as set forth above.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIGURE 1 is a cut-away view of a gas turbine engine in accordance with the present invention,
FIGURE 2 is a part sectional view of part of the engine of FIGURE 1, taken in line 2-2 of that figure,
FIGURE 3. is a part sectional view of part of the components shown in FIGURE 2 taken in line 3--3 of that figure, and
FIGURE 4 is a general view of the components shown in FIGURES 2 and 3.
Referring to the drawings, a gas turbine engine includes a compressor 11 comprising rows of rotor blades 12, 13, 14, 15, rows of stator vanes 16, 17 and 18 and external casing 20. Rotor blades 12 and 13 are mounted on rotor discs 21, 22, attached to a rotor shaft 23. Rotor blades 14, 15 are mounted on rotor discs 24, 25 attached to rotor shaft 26.
Stator vanes 16 are disposed between the rows of rotor blades 12 and 13 and are connected to an external annular casing member 30, which forms part of the casing 20 of the compressor, and to an internal annular member 31. The annular member 31 is connected to a bearing 32 within which shaft 23 is journalled. Thus the row of stator vanes 16 supports the bearing 32 and the rotor shaft 23.
3,339,833 Patented Sept. 5, 1967 As more clearly shown in FIGURES 2 to 4, casing member 30 is substantially U-shaped in cross-section, having side walls 33, 34 and a base 35. An annular boss 36 is disposed between side walls 33, 34, on the external surface 37 of base 35.
Casing member 30 is provided with a plurality of axially extending, angularly spaced apart, dove-tail slots 38 within which are disposed corresponding dove-tail roots 40 of stator vanes 16. It will be seen that the roots 40 are somewhat larger, in radial dimension, than the base 35, they therefore project above the external surface 37. The roots 40 project above surface 37 for a major portion of their axial length and they define, with external surface 37, two angled portions 41, 42 in which bonding material (not shown) is disposed to bond the roots 40 to external surface 37. Thus the stator vanes 16 are A fastened to the external casing member 30 by their dovetail joints and by bonding material.
The compressor 11 may be formed of metal e.g. a light alloy, in which case the roots 40 may be bonded, brazed or welded to the external surface 37. Alternatively, the compressor 11 may be formed of fibre reinforced synthetic resin material, in which case the roots 40 are bonded to external surface 37 by an adhesive or by further fibre reinforced synthetic resin material fused to both the roots 40 and the external surface 37.
It will be appreciated that, since the roots 40 project through the casing member 30, and are visible from outside the casing 20 of the compressor, the bonding process may be performed after the vanes have been assembled. The bonding process is also relatively easy, since the surfaces to be bonded are readily accessible.
As seen in FIGURES 2 and 3, the internal annular member 31 is also substantially U-shaped in cross-section, having spaced radial flanges 50, 51 and a base 52. The annular member 31 is provided with a plurality of axially extending, angularly spaced apart dove-tail slots 54 within which dove-tail root portions 55 of vanes 16 are disposed. The root portions 55 also extend through the base 52 and project above the surface 56 of annular member 31, as described above with reference to roots 40 and member 30. Thus root portions 55 are bonded to the surface 56 by adhesive or by brazing or welding, for example, and by their dove-tail connections.
Although only the row of stator vanes 16 are attached to their supporting members by the particular dove-tail connections described above, it will be appreciated that any stator vane or rotor blade may be so connected to its supporting member. Thus stator vanes 17 and 18 may be connected to the casing 20 in this manner and rotor blades 12, 13, 14 and 15 may be connected to rotor discs 21, 22, 24, 25 respectively, in a similar manner.
Also, the same method of connecting blades to their supporting member may be used for any axial fluid fiow machine which uses bladed rotors and stators e.g. turbines, fans and propellers.
We claim:
1. An axial fluid flow machine comprising concentric inner and outer annular mounting members, angularly spaced apart dove-tail slots in each said mounting member, the slotsin one mounting member being inclined and oppositely disposed from the outer and inner sides of the support members with respect to the slots in the other mounting member, a plurality of radially disposed blades extending between said members, each blade having a working portion and having a root portion at each end thereof, the root portions of each blade being of dove-tail shape and being disposed within and extending radially through said dove-tail slots to lock and support the blades against movement radially and axially, said root portions projecting radially from the surfaces of said mounting members remote from the working portion of each blade,
and being bonded to the said surfaces of the mounting members.
2. A machine as claimed in claim 1 wherein said inner mounting member provides a bearing support.
3. An axial fluid flow machine as claimed in claim 1 in which said blades are stator blades and the said C011- centric mounting members comprise inner and outer stator casings.
4. An axial fluid flow machine as claimed in claim 1 in which the said mounting members are generally U- shaped in axial cross section.
5. An axial fluid flow machine as claimed in claim 1 in which said blades are formed of fibre-reinforced synthetic resin material.
6. An axial fluid flow machine as claimed in claim 5 in which said annular mounting members are formed of fibre-reinforced synthetic resin material and the projecting root portions of said blades are bonded to the said surfaces of the mounting members by adhesive.
References Cited UNITED STATES PATENTS 6/1950 Price 230133 6/ 1954 Wosika 25378 1/1959 Hampshire et al. 25377 5/1960 Warnken 253-77 7/1960 Stadthaus et al. 25377 8/1961 Warnken 25377 1/1964 Robinson et a1 238133 FOREIGN PATENTS 9/ 1952 Australia. 4/1960 Canada. 11/1951 Great Britain.
DONLEY J. STOCKING, Primary Examiner.
HENRY F. RADUAZO, Assistant Examiner.

Claims (1)

1. AN AXIAL FLUID FLOW MACHINE COMPRISING CONCENTRIC INNER AND OUTER ANNULAR MOUNTING MEMBERS, ANGULARLY SPACED APART DOVE-TAIL SLOTS IN EACH SAID MOUNTING MEMBER, THE SLOTS IN ONE MOUNTING MEMBER BEING INCLINED AND OPPOSITELY DISPOSED FROM THE OUTER AND INNER SIDES OF THE SUPPORT MEMBERS WITH RESPECT TO THE SLOTS IN THE OTHER MOUNTING MEMBER, A PLURALITY OF RADIALLY DISPOSED BLADES EXTENDING BETWEEN SAID MEMBERS, EACH BLADE HAVING A WORKING PORTION AND HAVING A ROOT PORTION AT EACH END THEREOF, THE ROOT PORTIONS OF EACH BLADE BEING OF DOVE-TAIL SHAPE AND BEING DISPOSED WITHIN AND EXTENDING RADIALLY THROUGH SAID DOVE-TAIL SLOTS TO LOCK AND SUPPORT THE BLADES AGAINST MOVEMENT RADIALLY AND AXIALLY, SAID ROOT PORTIONS PROJECTING RADIALLY FROM THE SURFACES OF SAID MOUNTING MEMBERS REMOTE FROM THE WORKING PORTION OF EACH BLADE, AND BEING BONDED TO THE SAID SURFACES OF THE MOUNTING MEMBERS.
US441143A 1963-12-04 1965-03-19 Axial fluid flow machine such as a compressor or turbine Expired - Lifetime US3339833A (en)

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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3997280A (en) * 1974-06-21 1976-12-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Stators of axial turbomachines
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
FR2642113A1 (en) * 1989-01-20 1990-07-27 Rolls Royce Plc Method for manufacturing a set of fixed-blading fins for an axial-flow compressor and set of fins obtained by this method
US5022822A (en) * 1989-10-24 1991-06-11 United Technologies Corporation Compressor blade attachment assembly
US5083900A (en) * 1989-11-15 1992-01-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbomachine stator element
US20050129514A1 (en) * 2003-06-30 2005-06-16 Snecma Moteurs Nozzle ring with adhesive bonded blading for aircraft engine compressor
DE102004005237B4 (en) * 2004-02-03 2007-03-01 Mtu Aero Engines Gmbh Guide vane grille of a gas turbine
US20070248463A1 (en) * 2006-04-19 2007-10-25 United Technologies Corporation Wedge repair of mechanically retained vanes
US20080063521A1 (en) * 2006-09-06 2008-03-13 William Bogue Curved variable pitch wedge retention in vane outer base
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
FR2958680A1 (en) * 2010-04-13 2011-10-14 Snecma Intermediate casing for multi-flow turbojet engine, has fin whose end is in form of tongues adapted to be integrated with inner and outer shells arranged opposite to fin end based on dovetail type fastener
US20150104298A1 (en) * 2013-10-11 2015-04-16 Rolls-Royce Plc Tip treatment bars in a gas turbine engine
US9593586B2 (en) 2013-04-05 2017-03-14 Rolls-Royce Plc Vane assembly and method of making the same
US20180340433A1 (en) * 2017-05-24 2018-11-29 Doosan Heavy Industries & Construction Co., Ltd. Vane assembly and gas turbine including the same
US11156109B2 (en) 2019-08-13 2021-10-26 Ge Avio S.R.L Blade retention features for turbomachines
US11414994B2 (en) 2019-08-13 2022-08-16 Ge Avio S.R.L. Blade retention features for turbomachines
US11549379B2 (en) 2019-08-13 2023-01-10 Ge Avio S.R.L. Integral sealing members for blades retained within a rotatable annular outer drum rotor in a turbomachine

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Publication number Priority date Publication date Assignee Title
AU148304B (en) * 1904-09-07 1905-07-18 Magnus Philip An improvement in pneumatic tires
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction
GB660383A (en) * 1949-02-23 1951-11-07 Winnett Boyd Blade mounting for axial-flow compressors and the like
US2681788A (en) * 1951-05-23 1954-06-22 Solar Aircraft Co Gas turbine vane structure
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
CA596392A (en) * 1960-04-19 General Motors Corporation Compressor vane assembly and method of manufacture
US2937805A (en) * 1952-12-15 1960-05-24 Studebaker Packard Corp Stator blade assembly and method and machine for making same
US2944326A (en) * 1955-06-02 1960-07-12 Gen Electric Method of staking blades
US2995294A (en) * 1954-12-02 1961-08-08 Studebaker Packard Corp Stator casing and blade assembly
US3118593A (en) * 1961-05-03 1964-01-21 Rolls Royce Fluid flow machine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA596392A (en) * 1960-04-19 General Motors Corporation Compressor vane assembly and method of manufacture
AU148304B (en) * 1904-09-07 1905-07-18 Magnus Philip An improvement in pneumatic tires
US2510606A (en) * 1943-05-22 1950-06-06 Lockheed Aircraft Corp Turbine construction
GB660383A (en) * 1949-02-23 1951-11-07 Winnett Boyd Blade mounting for axial-flow compressors and the like
US2681788A (en) * 1951-05-23 1954-06-22 Solar Aircraft Co Gas turbine vane structure
US2937805A (en) * 1952-12-15 1960-05-24 Studebaker Packard Corp Stator blade assembly and method and machine for making same
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
US2995294A (en) * 1954-12-02 1961-08-08 Studebaker Packard Corp Stator casing and blade assembly
US2944326A (en) * 1955-06-02 1960-07-12 Gen Electric Method of staking blades
US3118593A (en) * 1961-05-03 1964-01-21 Rolls Royce Fluid flow machine

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3997280A (en) * 1974-06-21 1976-12-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Stators of axial turbomachines
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
FR2642113A1 (en) * 1989-01-20 1990-07-27 Rolls Royce Plc Method for manufacturing a set of fixed-blading fins for an axial-flow compressor and set of fins obtained by this method
US5022822A (en) * 1989-10-24 1991-06-11 United Technologies Corporation Compressor blade attachment assembly
US5083900A (en) * 1989-11-15 1992-01-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbomachine stator element
US7553130B1 (en) 2003-06-30 2009-06-30 Snecma Nozzle ring adhesive bonded blading for aircraft engine compressor
US20090148283A1 (en) * 2003-06-30 2009-06-11 Snecma Moteurs Nozzle ring adhesive bonded blading for aircraft engine compressor
US20050129514A1 (en) * 2003-06-30 2005-06-16 Snecma Moteurs Nozzle ring with adhesive bonded blading for aircraft engine compressor
US7147434B2 (en) * 2003-06-30 2006-12-12 Snecma Moteurs Nozzle ring with adhesive bonded blading for aircraft engine compressor
DE102004005237B4 (en) * 2004-02-03 2007-03-01 Mtu Aero Engines Gmbh Guide vane grille of a gas turbine
US20070248463A1 (en) * 2006-04-19 2007-10-25 United Technologies Corporation Wedge repair of mechanically retained vanes
US7510372B2 (en) * 2006-04-19 2009-03-31 United Technologies Corporation Wedge repair of mechanically retained vanes
US7665963B2 (en) * 2006-09-06 2010-02-23 United Technologies Corporation Curved variable pitch wedge retention in vane outer base
US20080063521A1 (en) * 2006-09-06 2008-03-13 William Bogue Curved variable pitch wedge retention in vane outer base
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
FR2958680A1 (en) * 2010-04-13 2011-10-14 Snecma Intermediate casing for multi-flow turbojet engine, has fin whose end is in form of tongues adapted to be integrated with inner and outer shells arranged opposite to fin end based on dovetail type fastener
US9593586B2 (en) 2013-04-05 2017-03-14 Rolls-Royce Plc Vane assembly and method of making the same
US20150104298A1 (en) * 2013-10-11 2015-04-16 Rolls-Royce Plc Tip treatment bars in a gas turbine engine
US9957976B2 (en) * 2013-10-11 2018-05-01 Rolls-Royce Plc Tip treatment bars in a gas turbine engine
US20180340433A1 (en) * 2017-05-24 2018-11-29 Doosan Heavy Industries & Construction Co., Ltd. Vane assembly and gas turbine including the same
US10662790B2 (en) * 2017-05-24 2020-05-26 Doosan Heavy Industries Co., Ltd. Vane assembly and gas turbine including the same
US11156109B2 (en) 2019-08-13 2021-10-26 Ge Avio S.R.L Blade retention features for turbomachines
US11414994B2 (en) 2019-08-13 2022-08-16 Ge Avio S.R.L. Blade retention features for turbomachines
US11549379B2 (en) 2019-08-13 2023-01-10 Ge Avio S.R.L. Integral sealing members for blades retained within a rotatable annular outer drum rotor in a turbomachine
US11885237B2 (en) 2019-08-13 2024-01-30 Ge Avio S.R.L. Turbomachine including a rotor connected to a plurality of blades having an arm and a seal

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