EP2394786A2 - Outil de finition de composants de turbomachine - Google Patents
Outil de finition de composants de turbomachine Download PDFInfo
- Publication number
- EP2394786A2 EP2394786A2 EP11169379A EP11169379A EP2394786A2 EP 2394786 A2 EP2394786 A2 EP 2394786A2 EP 11169379 A EP11169379 A EP 11169379A EP 11169379 A EP11169379 A EP 11169379A EP 2394786 A2 EP2394786 A2 EP 2394786A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- base
- finishing tool
- turbomachine
- finishing
- component
- 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.)
- Withdrawn
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/009—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding profiled workpieces using a profiled grinding tool
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/02—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding grooves, e.g. on shafts, in casings, in tubes, homokinetic joint elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B33/00—Honing machines or devices; Accessories therefor
- B24B33/05—Honing machines or devices; Accessories therefor designed for working grooves, e.g. in gun barrels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B33/00—Honing machines or devices; Accessories therefor
- B24B33/08—Honing tools
- B24B33/088—Honing tools for holes having a shape other than cylindrical
Definitions
- This disclosure relates generally to a finishing tool. More particularly, but not exclusively, this disclosure relates to a finishing tool having a superabrasive that is used to finish a turbomachine component.
- Turbomachines such as gas turbine engines, are known.
- a typical turbomachine includes multiple sections, such as a fan section, a compression section, a combustor section, and a turbine section.
- the fan section moves air into the turbomachine. Some of the air is compressed. The compressed air is then mixed with fuel and combusted in the combustor section. Products of the combustion are expanded in the turbine section to rotatably drive the turbomachine.
- turbomachines include blades mounted within rotor slots.
- the blades rotate with the rotors in the compression section and the turbine section, for example.
- Nonconformances and variations in the surfaces of the rotor slots can affect performance of the turbomachine.
- a surface of a rotor slot that varies from a desired dimension can introduce stress concentrations in the rotor or in a blade mounted within that slot.
- Nonconformances and variations within the surface of the rotors defining the blade slots are often difficult to identify and eliminate.
- Nonconformances include geometric and metallurgical.
- An example finishing tool form assembly includes a base and a superabrasive bonded to a surface of the base.
- the superabrasive is configured to be reciprocated with the base relative to a longitudinally extending recess of a component to finish at least one surface of the component.
- An example turbomachine component finishing tool assembly includes a fixture and a form mountable to the fixture.
- the form includes an abrasive bonded to a base.
- the fixture is configured to reciprocate the form relative to a surface of a turbomachine component.
- An example turbomachine surface finishing method includes reciprocating a base relative to a surface of a turbomachine component. The method finishes the surface with an abrasive bonded to the reciprocating base.
- Figure 1 schematically illustrates an example aircraft gas turbine engine 10, which is an example type of turbomachine.
- the example gas turbine engine 10 includes (in serial flow communication) a fan section 14, a low pressure compressor 18, a high pressure compressor 22, a combustor 26, a high pressure turbine 30, and a low pressure turbine 34.
- the gas turbine engine 10 is circumferentially disposed about an engine centerline X.
- air is pulled into the gas turbine engine 10 by the fan section 14. Some of the air moves through a flow path 36 to a core of the gas turbine engine 10.
- the air moving through the flow path 36 is pressurized by the compressors 18 and 22, mixed with fuel, and burned within the combustor 26.
- the turbines 30 and 34 extract energy from the hot combustion gases flowing from the combustor 26.
- the high pressure turbine 30 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 22 through a high speed shaft 38
- the low pressure turbine 34 utilizes the extracted energy from the hot combustion gases to power the low pressure compressor and the fan section 14 through a low speed shaft 42.
- a rotor 46 within the low pressure compressor 18 of the engine 10 includes a plurality of slots 50.
- the slots 50 are configured to receive the root section of the blades (not shown). The blades rotate with the rotor 46 within the low pressure compressor 18 of the engine 10. The blades pressurize air moving through the flow path 36 in a known manner.
- the rotor 46 is milled to establish the slots 50.
- the slots 50 are finished, in this example, to remove nonconformances from a surface 54 after the milling.
- the surface 54 of the rotor 46 defines portions of the slots 50.
- a form 58 is received within one of the slots 50a during finishing.
- a fixture 62 reciprocates the form 58 along an axis X1.
- the slot 50a extends along an axis X2 that is parallel to the axis X1.
- the rotor 46 is rotated relative to the fixture 62, and the form is received within another of the slots 50.
- portions of the form 58 corresponding to the surface 54 includes an abrasive 66 bonded to a base 70. As the form 58 reciprocates relative to the slot 50a, the abrasive 66 finishes the surface 54 of the slot 50a.
- the fixture 62 reciprocates the form 58 for a controlled stroke and for an established length of time. Increasing the length of time increases the amount of material removed from the rotor 46, for example.
- Finishing removes or reduces nonconformances in the surfaces 54 of the slot 50 by removing about .001 inches (0.0254 mm) of material from the surface 54 of the rotor 46. In other examples, finishing removes nonconformances in other areas of the slot 50a, such as a surface 56, a surface 57, or removes a different amount of material
- Example nonconformances include geometric nonconformances or variations in the position of the surface 54 of the slot 50a from a desired position of the surface 54. Other example nonconformances are the result of the interfaces between portions of the slot 50a machined by different milling cutters.
- the example slots 50 have an enlarged portion 74 and a narrower neck portion 78. During operation of the engine 10, the root portions of the blades having a similar shape are received within the slots 50. As can be appreciated, the shape of the slots 50 limits movement of the blades radially away from the rotor 46.
- the form 58 has a cross-sectional profile similar to the cross-sectional profile of the base of the blade. That is, the form 58 includes an enlarged portion 82 and a narrowed portion 86.
- the base 70 of the form 58 is a cast iron material
- the abrasive 66 which is mounted to the enlarged portion 74 of the finishing form, is a superabrasive.
- the example abrasive 66 is a cubic boron nitride abrasive that is 400 grit ASTM.
- Superabrasives are typically harder than conventional abrasives.
- conventional abrasives include pumice, sand, and silicon carbides.
- Superabrasives by contrast, include diamond and the aforementioned cubic boron nitride.
- a plating process such as a nickel plating process, is used to bond a layer of the example abrasive 66 to the base 70.
- the base 70 is about 0.0015 inches (0.0381 mm). undersized relative to the slots 50.
- the abrasive 66 has a thickness of about 0.0015 inches (0.381 mm) when bonded to the base 70. Adding the abrasive 66 makes the thickness of the enlarged portion 82 of the form 58 to be about the same as the enlarged portion 74 of the slots 50.
- a spring 90 housed within the fixture is used to bias the form 58 toward a radial center of the rotor 46. This facilitates the form 58 maintaining contact with the surface 54. Material removal rates can be controlled via variations in spring compression and spring stiffness.
- a spring 90a is biased toward a roller 44, which biases a form 58a toward a radial center of a rotor.
- features of the disclosed examples include a low cost, high precision process that can rework slots and other turbomachine components rather than rebroaching an entire rotor slot, for example.
- Another feature of the disclosed examples is reducing the scrap rate of turbomachine components due to nonconformances in their surfaces.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Polishing Bodies And Polishing Tools (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/814,477 US20110306275A1 (en) | 2010-06-13 | 2010-06-13 | Component finishing tool |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2394786A2 true EP2394786A2 (fr) | 2011-12-14 |
EP2394786A3 EP2394786A3 (fr) | 2014-08-13 |
Family
ID=44514454
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11169379.2A Withdrawn EP2394786A3 (fr) | 2010-06-13 | 2011-06-09 | Outil de finition de composants de turbomachine |
Country Status (2)
Country | Link |
---|---|
US (1) | US20110306275A1 (fr) |
EP (1) | EP2394786A3 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2018219587A1 (fr) * | 2017-05-29 | 2018-12-06 | Siemens Aktiengesellschaft | Procédé pour le nettoyage d'une rainure de réception de pied d'aube |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110575852B (zh) * | 2019-07-25 | 2020-08-11 | 浙江大学 | 一种集成样品前处理的多重数字rpa微流控芯片 |
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-
2011
- 2011-06-09 EP EP11169379.2A patent/EP2394786A3/fr not_active Withdrawn
Non-Patent Citations (1)
Title |
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None |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2018219587A1 (fr) * | 2017-05-29 | 2018-12-06 | Siemens Aktiengesellschaft | Procédé pour le nettoyage d'une rainure de réception de pied d'aube |
Also Published As
Publication number | Publication date |
---|---|
US20110306275A1 (en) | 2011-12-15 |
EP2394786A3 (fr) | 2014-08-13 |
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