• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    gas turbine engine, and, method for retaining a part to an engine frame structure. a gas turbine engine includes an engine frame structure and a retaining block assembly. the engine frame structure includes a cavity that receives the retaining block assembly. the retainer block assembly includes a stop block and a pin which retains the stop block within the cavity. the stop block is slack with respect to the pin.
    公开号:BR102012029658B1
    申请号:R102012029658-6
    申请日:2012-11-21
    公开日:2021-06-01
    发明作者:Conway Chuong；Kurt P. Werner；Shelton O. Duelm
    申请人:United Technologies Corporation；
    IPC主号:
    专利说明:

    FOUNDATION
    [0001] This description relates to a gas turbine engine and more particularly to the retention of a part in relation to an engine frame structure.
    [0002] Gas turbine engines typically include at least a compressor section, a combustor section and a turbine section. During operation, air is pressurized in the compressor section and is mixed with the fuel and combusted in the combustor section to generate hot flue gases. The hot flue gases are communicated through the turbine section, which extracts energy from the hot flue gases to power the compressor section and other loads of the gas turbine engine.
    [0003] One or more sections of the gas turbine engine may include a plurality of sets of blades that have blades interspersed between rotor sets that carry the blades of successive stages of the section. Each vane in a vane set must be retained in an engine frame structure for proper functioning during gas turbine engine operation. Flaps, hooks, and other features are typically incorporated into the design of the reeds to achieve this retention. SUMMARY
    [0004] A gas turbine engine includes an engine frame frame and a retaining block assembly. The engine frame structure includes a cavity that accommodates the retaining block assembly. The retainer block assembly includes a stop block and a pin that retains the stop block in the cavity. The stop block is loose in relation to the pin.
    [0005] In another embodiment taken as an example, a gas turbine engine includes a compressor section, a combustor section and a turbine section, each arranged around an engine centerline axis. An engine frame structure is associated with at least a portion of the compressor section and the turbine section. At least one of the compressor section and the turbine section includes a part and a retaining block assembly that circumferentially retains the part related to the engine frame structure.
    [0006] In yet another embodiment taken by way of example, a method for retaining a part to an engine frame structure includes providing a cavity in the engine frame structure, inserting a stop block in the cavity and retaining the stop block in the cavity with a pin. The pin is trapped by a portion of the piece.
    [0007] The various features and advantages of this description will become evident to those skilled in the art from the detailed description below. The drawings accompanying the detailed description can be briefly described as follows. BRIEF DESCRIPTION OF THE DRAWINGS
    [0008] Figure 1 illustrates, schematically, a gas turbine engine.
    [0009] Figures 2A and 2B illustrate a portion of a gas turbine engine.
    [00010] Figure 3 illustrates an example of a retaining block set to retain a vane of a set of vanes.
    [00011] Figures 4A and 4B illustrate additional features of the retaining block of the retaining block assembly of figure 3.
    [00012] Figures 5A and 5B illustrate a stop block of a retaining block assembly.
    [00013] Figure 6 illustrates a rear section view (looking forward) of a blade assembly of a gas turbine engine.
    [00014] DETAILED DESCRIPTION
    [00015] Figure 1 schematically illustrates a gas turbine engine 10. The example of gas turbine engine 10 is a two-spool (shaft) turbofan engine that generally incorporates a fan section 14, a section of compressor 16, a combustor section 18 and a turbine section 20. Alternative engines may include some or additional sections, such as an amplifier section (not shown) among other systems or features. Generally the fan section 14 drives air along a bypass flow path while the compressor section 16 drives air along a core flow path for compression and communication to the combustor section 18. The hot flue gases generated in the combustor section 18 are expanded through the turbine section 20. This view is highly schematic, and is included to provide a basic understanding of the gas turbine engine 10, not to limit the description. This description extends to all types of gas turbine engines and all types of applications including but not limited to three-spool turbofan configurations.
    [00016] The gas turbine engine 10 generally includes at least one low speed reel 22 and one high speed reel 24, mounted for rotation around an engine centerline axis 12 relative to a static structure of the engine. motor 27 through various bearing systems 29. Low speed spool 22 generally includes an inner shaft 31 which interconnects a fan 33, a low pressure compressor 17 and a low pressure turbine 21. The inner shaft 31 can connect to fan 33 via a geared architecture 35 to drive fan 33 at a slower speed than the low speed spool 22. Although the geared architecture 35 is schematically delineated between the fan 33 and the low pressure compressor 17, it should be understood that the geared architecture 35 could be disposed at any location of the gas turbine engine that includes, but is not limited to, adjacent to the t. low pressure turbine 21. The high speed spool 24 includes an outer shaft 37 which interconnects a high pressure compressor 19 and a high pressure turbine 23.
    [00017] A combustor 15 is arranged between the high pressure compressor 19 and the high pressure turbine 23. The inner shaft 31 and the outer shaft 37 are concentric and rotate around the centerline axis of the engine 12. A flow of core air is compressed by the low-pressure compressor 17 and the high-pressure compressor 19, is mixed with fuel and burned inside the combustor 15, and is then expanded over the high-pressure turbine 23 and the low-pressure turbine 21. turbines 21, 23 rotate the low pressure spool 22 and the high pressure spool 24 in response to expansion.
    [00018] The compressor section 16 and the turbine section 20 may each include alternate rows of rotor assemblies 39 and vane assemblies 21. The rotor assemblies 39 carry a plurality of rotating blades, while each vane assembly 41 includes a plurality of stator vanes. The blades of the rotor assemblies 39 create or extract energy (in the form of pressure) from the air flow that is communicated through the turbine engine 10. The blades of the blade assemblies 41 direct airflow to the blades of the rotor assemblies 39 or to add or to extract energy. Each vane of vane sets 41 is circumferentially retained to the gas turbine engine 10 as discussed further below.
    [00019] Figures 2A and 2B illustrate a portion 100 of a gas turbine engine 10. In this example, the illustrated portion 100 is from the turbine section 20. However, this description is not limited to the turbine section 20, and could extend to other sections of the gas turbine engine 10, including but not limited to compressor section 16.
    [00020] Portion 100 includes a piece such as a vane assembly 41. Vane assembly 41 includes a plurality of vanes 40 (only one shown) that are circumferentially disposed (inward and outward of the page of Figure 2A) upon around the centerline axis of the engine 12. Each vane 40 includes an airfoil 42 that extends between an inner platform 44 and an outer platform 46. The vane assembly 41 is connected to an engine frame structure 49 associated with the portion 100 of the gas turbine engine 10, such as between an outer casing structure 48 and an inner ring structure 50. The inner ring structure 50 could be a portion of a rotor assembly of an adjacent rotor assembly 39, or it could be a separate structure together.
    [00021] The reed 40 can be a stationary reed or a variable reed, and could be cantilevered. Vanes 40 of vane assembly 41 extend between a leading edge 53 and a trailing edge 54. The gas turbine engine 10 establishes a gas path 56 for communicating core air flow extending in a direction from the leading edge 52 towards the rear edge 54 of the vane 40.
    [00022] The vane 40 is circumferentially retained within the gas turbine engine 10 by means of a retaining block assembly 58. Although delineated as a vane, it should be understood that the retaining block assembly 58 could be used to retain any part of the gas turbine engine. The retaining block assembly 58 is received in a cavity 60 of the engine frame structure 49. As used in this description, the term "engine frame structure" may refer to the outer frame structure 48, the inner ring structure 50 , or any other portion of the static structure of the motor 27. In other words, the retaining block assembly 58 can be implemented in the outer casing structure 48, the inner ring structure 50, or both, to circumferentially retain the vane 40 of the vane assembly 41 within portion 100 of the gas turbine engine 10. Each vane 40 of vane assembly 41 may be retained circumferentially using the one or more retainer block assemblies 58. Cavity 60 may be machined, milled, cast , or otherwise formed on the motor frame structure 49, in any known manner.
    [00023] The retaining block assembly 58 includes a stop block 62 and a pin 64 which retains the stop block 62 within cavity 60. A reed hook 66 is partially received by a carcass hook 48 of the carcass structure of engine 49. Reed hook 66 is positioned radially on the inner edge of retainer block assembly 58 in the installed state. Reed hook 66 engages pin 64 with respect to stop block 62. In one example, pin 64 is secured radially to stop block 62 via reed hook 66.
    [00024] During engine operation, the circumferential pressure loads from the vane 40 are transferred to the retaining block assembly 58, which is then transferred to the engine frame structure 49. In other words, the pin 64 is substantially free from mechanical loading during engine operation. Inner platform 44 and outer platform 46 of vane 40 may include a variety of other retaining features, such as vane hooks, tabs, legs, flanges, and other parts, to achieve radial and axial attachment of vane 40 to the vane structure. motor frame 49. These features can work independently of the circumferential retaining feature taken as an example, or can work in a fixed way with it, and provide combined degrees of restriction.
    [00025] Figure 3 illustrates a cross-sectional view of the retaining block assembly 58 introduced in Figures 2A and 2B. Stop block 62 is received within cavity 60 in engine frame structure 49. Alternatively, stop block 62 could be incorporated as part of engine frame structure 49. In other words, stop block 62 it could be a separate structure from the engine frame structure 49, or it could be formed integrally as part of the engine frame structure 49.
    [00026] Pin 64 retains stop block 62 within cavity 60. Pin 64 is inserted through a hole 90 of stop block 62, and can be press-fit into an opening 76 of motor frame frame 49 A body portion 74 of pin 64 extends into opening 76 of motor frame frame 49. Hole 90 is oversized relative to pin 64, i.e., hole 90 is of a diameter greater than the diameter. of pin 64. Hole 90 is oversized to create gap 72 and allow for the relative freedom of stop block 62 to pin 64 and cavity 60. Unlike snap pin 64, retaining block assembly 58 is otherwise free of mechanical connections that include screws or studs to circumferentially retain vanes 40 of vane assembly 41. Vane hook 66 provides a secondary retaining feature that prevents pin 64 from disengaging from retaining block assembly 58 (to see figure 2B).
    [00027] A first flange 70 extending from the body portion 74 of the pin 64 contacts (i.e., top) against the motor frame structure 49 at an interface 51. The space 72 extends between the stop block 62 and pin 64 such that stop block 62 is loosened relative to pin 64 (as well as motor frame structure 49). Gap 72 allows stop block 62 to move in a radial and circumferential direction relative to pin 64 during gas turbine engine operation, thus allowing pin 64 to be substantially free of mechanical loading during operation. Actual dimensions of range 72 may vary, and are dependent on application and manufacturing tolerances, among other factors.
    [00028] The pin 64 includes a second flange 71 which is received by a countersunk portion 92 of the stop block 62. The second flange 71 is radially inward from the first flange 60. The second flange 71 establishes a second diameter D2 which is larger than a first diameter D1 of the first flange 70 which retains the stop block 62 for release in the radial direction.
    [00029] The pin 64 may also include an inner portion 78 that is pierced through the pin. Inner portion 78 may optionally include threads 80 that allow easy removal of pin 64 from retainer block assembly 58.
    [00030] Figures 4A and 4B illustrate the retaining block assembly 58 with the vane 40 removed to better illustrate the features of the retaining block assembly 58. Both the cavity 60 and the stop block 62 may include a shape generically rectangular. The matched geometry of the cavity 60 and the stop block 62 substantially prevents the rotation of the stop block 62 within the cavity 60 during engine operation. Cavity 60 and stop block 62 may include other geometries and configurations. Pin 64 is flush with or below a surface 82 of stop block 62 in the installed state illustrated by Figures 4A and 4B. Surface 82 faces vane 40 when vane 40 is in an installed state.
    [00031] In one example, the engine frame structure 49, the stop block 62 and the pin 64 are each manufactured from the same type of material to reduce any thermal mismatch between the parts during engine operation. Using the same material helps to establish the gap 72. An example of a material is a nickel alloy. However, other materials are also considered to be within the scope of this description.
    [00032] Figures 5A and 5B illustrate an example stop block 62 of the retainer block assembly 58 detailed above. Stop block 62 includes a first block portion 84, and a second block portion 86 protruding from the first block portion 84. In one example, the second block portion 86 protrudes perpendicularly from the first block portion. block 84. Stop block 62 may include a monolithic structure, or could be assembled by securing second block portion 86 to first block portion 84, in any known manner.
    [00033] The first block portion 84 is received within cavity 60 and is flush with or below an outer surface 88 of cavity 60 (see figures 4A and 4B). Cavity 60 has close tolerance for first block portion 84 to minimize loose fit between first block portion 84 and cavity 60. The dimension, shape, and geometry of cavity 60 and stop block 62 could vary depending on parameters specific design, and other design criteria.
    [00034] The first block portion 84 includes a hole 90 extending through the first block portion 84. The hole 90 includes a countersunk portion 92. The second flange 71 of the pin 64 is received within the countersink portion 92 of the first portion block 84 (see figure 3). The first block portion 84 may also include rounded corners 96.
    [00035] The second block portion 86 protrudes from the first block portion 84 in a direction towards the vane 40 (see figures 4A and 4B and figure 6). The second block portion 86 may include portions 87 that extend radially beyond a width W of the first block portion 84. The second block portion 86 may also include at least one chamfered portion 98 which aids in the insertion of the vane 40 with respect to retaining block assembly 58, to circumferentially retaining vane 40 relative to engine frame structure 49. In this example, beveled portion 98 is defined at a corner 99 of second block portion 86.
    [00036] Referring to Figure 6, a portion of the vane 40 contacts the second block portion 86 of the stop block 62 to prevent circumferential rotation of the vane 40. In one example, the portion is a vane hook 66, although other parts and components are considered. The second block portion 86 extends into a secondary air cavity 156 which is radially outward from the gas path 56, while the first block portion 84 is radially outward from the secondary air cavity 156 (see also figure 2A).
    [00037] Although the different examples have the specific components shown in the illustrations, embodiments of this description are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another of the examples.
    [00038] The foregoing description is to be interpreted as illustrative and not in any limiting sense. A worker of ordinary skill in technique should understand that certain modifications could come within the scope of this description. For these reasons, the following claims should be studied to determine the true scope and content of this description.
    权利要求:
    Claims (9)
    [0001]
    1. A gas turbine engine, comprising: an engine frame structure (49) including a cavity (60); a retaining block assembly (58) received in the cavity (60); and, a vane (40) that is retained circumferentially with respect to the engine frame structure (49) by the retainer block assembly (58), where the retainer block assembly (58) includes a stop block ( 62) and a pin (64) which retains the stop block (62) in the cavity (60), characterized in that: the pin (64) is inserted through a hole in the stop block (62); and, the stop block (62) is slack relative to the pin (64).
    [0002]
    2. Gas turbine engine according to claim 1, characterized in that the pin (64) includes an inner portion (78) which is threaded.
    [0003]
    3. Gas turbine engine according to any one of claims 1 or 2, characterized in that a first flange (70) of the pin (64) contacts the engine frame structure (49).
    [0004]
    4. Gas turbine engine according to claim 4, characterized in that a second flange (71) of the pin (64) is received within a countersunk portion (92) of a bore of the stop block (62).
    [0005]
    5. Gas turbine engine according to any one of claims 1 to 4, characterized in that the stop block (62) includes a first block portion (84) and a protruding second block portion (86) from the first block portion (84).
    [0006]
    6. Gas turbine engine according to claim 5, characterized in that the second block portion (86) includes a beveled portion (98).
    [0007]
    7. Gas turbine engine according to any one of claims 5 or 6, characterized in that a portion of a vane (40) contacts the second portion of block (86).
    [0008]
    8. Gas turbine engine according to any one of claims 1 to 7, characterized in that the pin (64) is radially trapped relative to the stop block (62) with a reed hook (66).
    [0009]
    9. Gas turbine engine according to claim 8, characterized in that the vane hook (66) is received axially by a frame hook (68) of the engine frame structure (49).
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    CN103161578A|2013-06-19|
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    法律状态:
    2018-03-06| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-03-13| B25G| Requested change of headquarter approved|Owner name: UNITED TECHNOLOGIES CORPORATION (US) |
    2018-12-04| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-12-17| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-05-04| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-06-01| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 21/11/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/324,110|2011-12-13|
    US13/324,110|US8961125B2|2011-12-13|2011-12-13|Gas turbine engine part retention|
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