• 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:
    An airflow inlet (100) includes an inlet nozzle component (104) having a substantially uneven interior surface (132) and a coating (102) of varying thickness in a gauge annulus area (130) of the substantially uneven interior surface (132). The measuring annulus area (130) merely includes an annulus around the inner surface (132) of the inlet nozzle component (104). The coating (102) of varying thickness is configured to provide a more planar surface (132) than the substantially uneven inner surface (132).
    公开号:CH710050A2
    申请号:CH01174/15
    申请日:2015-08-14
    公开日:2016-02-29
    发明作者:Rex Allen Morgan；Stephen Ronald Watts
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION
    [0001] The disclosure generally relates to airflow inlets, and more particularly to an airflow inflow nozzle on which a coating is provided to reduce its surface roughness and a method associated therewith.
    Air flow inlets to industrial devices, such as e.g. Gas turbine compressors include a trumpet-shaped inflow nozzle component that acts to trap an airflow, initially compress and, e.g. in the direction of a turbine section of the compressor. In many devices, the static pressure in the trumpet-shaped inflow nozzle component is measured during operation using, for example, a pitot method. The static pressure can be used to determine an air mass flow, which is used to better control the operation of other components, such as air. in the control of a firing temperature of a combustion chamber of a gas turbine. In another example, a mass flow may be used to determine a degradation of compressor operating limits.
    A challenge in determining a static pressure in an inlet nozzle is that an inlet annulus area in which the pressure is measured must be accurately known. However, conventional inlet nozzles are often fabricated as molded components which have significant variation and large tolerances on their inner surface, i. they are uneven or rough. The variations and large inlet nozzle tolerances reduce the accuracy of the static pressure measured by a static pressure sensing system and thus prevent accurate mass flow calculations. To cope with this situation, a sample of the inlet nozzle (s) is conventionally analyzed after manufacture, and a calibrated correction factor is determined and used in calculating the static pressure for all the inlet nozzles. However, because there are large variations between the inlet nozzles that are generated, and because the inner surface of an inlet nozzle may change over time, the use of a sample correction factor is not ideal. While casting or machining of a low surface variation inlet nozzle is possible, it is generally not cost effective. Such a manufacturing approach also does not correct the problem for previously installed inlets.
    BRIEF DESCRIPTION OF THE INVENTION
    A first aspect of the disclosure provides an airflow inlet, comprising: an inlet nozzle component having a substantially uneven inner surface; and a coating of varying thickness in a measuring annulus area of the substantially uneven inner surface, wherein the coating of varying thickness is configured to have a more planar inner surface than the substantially uneven inner surface, the measuring annulus area merely surrounding an annulus around the inner surface of the inlet nozzle component contains.
    In the aforementioned airflow inlet, the coating may contain an epoxide.
    As an alternative to this, the coating may contain a plastic.
    As a further alternative, the coating may contain glass fiber.
    The airflow inlet of any of the aforementioned types may further include a static pressure sensing system configured to determine a static pressure of airflow through the inlet nozzle component using an annular space region based on the planar interior surface.
    In the airflow inlet of any type mentioned above, the inlet nozzle component may include a molded inlet nozzle component having a substantially uneven surface.
    The substantially uneven inner surface of any of the aforementioned airflow inlets may vary by up to 1.3 centimeters.
    In one embodiment, the measuring annulus area may include opposing beveled sides.
    In another embodiment, the annulus may include at least one strut which is at least partially covered by the coating of varying thickness.
    A second aspect of the disclosure provides an inflow nozzle component for an airflow inlet, the inflow nozzle component comprising: a static pressure annulus space configured to measure a static pressure by at least one sensor system, the annulus space area having a coating of varying thickness on a substantially contains uneven inner surface of the inlet nozzle component in only the measuring annulus area, wherein the coating of varying thickness is adapted to have a more planar surface than the substantially uneven inner surface within the Meßringraumbereich.
    In the aforementioned inflow nozzle component, the coating of varying thickness may be selected from a group including: an epoxy, a plastic and / or glass fiber.
    The inflow nozzle component may further comprise the at least one sensor system at the measuring annulus area configured to measure a static pressure of an air flow through the inflow nozzle component.
    In any of the aforementioned inlet nozzle components, the substantially uneven inner surface may vary by up to 1.3 centimeters.
    Additionally or alternatively, the inflow nozzle component may include a cast inflow nozzle component.
    In one embodiment of the inlet nozzle component, the measuring annulus area may include opposing beveled sides.
    In another embodiment of the inlet nozzle component, the annulus may include at least one strut which is at least partially covered by the coating of varying thickness.
    A third aspect of the disclosure provides a method comprising: accessing an inflow nozzle component of an airflow inlet, the inflow nozzle component including a substantially uneven interior surface; and applying a coating of varying thickness to a measuring annulus area of the substantially uneven inner surface of the inflow nozzle component to produce a more planar inner surface, the measuring annulus area containing only an annulus around the inner surface of the inflow nozzle component.
    In the aforementioned method, the measuring annulus area may include an annulus area at which a static pressure of an air flow through the inlet nozzle component is measured.
    Any of the aforementioned methods may further comprise checking a correction factor to determine a static pressure of an air flow through the inlet nozzle component, wherein the correction factor may initially be based on the substantially uneven inner surface.
    The illustrated aspects of the present disclosure are intended to solve the problems described herein and / or other problems not discussed.
    BRIEF DESCRIPTION OF THE DRAWINGS
    These and other features of the disclosure will become more readily apparent from the following detailed description of various aspects of the disclosure, taken in conjunction with the accompanying drawings, in which the drawings illustrate various embodiments of the disclosure, in which:<Tb> FIG. 1 <SEP> shows a cross-sectional view of an airflow inlet for a compressor, the airflow inlet including a coating on the measuring annulus area of the trumpet-shaped inlet nozzle component according to embodiments of the invention;<Tb> FIG. Figure 2 shows an enlarged cross-sectional view of a substantially uneven inner surface of an inlet nozzle component of the airflow inlet;<Tb> FIG. Figure 3 shows an enlarged cross-sectional view of an inner surface of the inlet nozzle component of the airflow inlet with a coating;<Tb> FIG. 4 and 5 show a cross-sectional view of airflow inlets having inlet nozzle components of varying shape and including a coating on a measuring annulus area according to embodiments of the invention;<Tb> FIG. Figure 6 shows an end view of one embodiment of an inlet nozzle component having a coating on its struts according to embodiments of the invention.
    It should be noted that the drawings of the disclosure are not to scale. The drawings are intended to illustrate only typical aspects of the disclosure, and therefore should not be taken as limiting the scope of the disclosure. In the drawings, like numbers represent like elements throughout the drawings.
    DETAILED DESCRIPTION OF THE INVENTION
    As indicated above, the disclosure provides an airflow inlet having a coating in a metering annulus area of an inlet nozzle component. Referring to FIG. 1, a cross-sectional view of an airflow inlet 100 is illustrated that includes a coating 102 of varying thickness on a trumpet-shaped inlet nozzle component 104 according to embodiments of the invention. The illustrative device for the airflow inlet 100 includes a compressor 110 for e.g. a gas turbine. The compressor 110 includes a turbine (or turbo fan) 112 for the intake of an airflow 114 into the inlet nozzle component 104. Injection nozzle component 104 may include any structure through which airflow initially flows as part of an inlet. In most, but not all cases, the trumpet-shaped inflow nozzle 104 serves to capture an airflow 114 and direct it to a turbine 112 where extensive compression occurs before the airflow is communicated to other components (not shown). The inlet nozzle component 104 can be identified using various alternative names, such as e.g. Inlet, compressor inlet, inlet fan, flow nozzle, etc. refer. As described herein, a static pressure sensing system 116 may be provided that is configured to determine a static pressure of the airflow 114 through the inlet nozzle component 104 in a gauge annulus or belt area 130. Other control systems (not shown) may use the pressure reading to determine a mass flow through the inlet 100 and / or to control other components. Although the device has been illustrated with respect to a compressor 110, it will be understood that the airflow inlet 100 as described herein may be used in a wide variety of air inlet systems.
    FIG. 2 shows an enlarged cross-sectional view of the inlet nozzle component 104 without a coating as taught herein. As illustrated, the inlet nozzle component 104 has a substantially uneven inner surface 120 that has a large amount of surface variation V. As used herein, "substantially uneven inner surface" refers to a non-smooth or rough surface that substantially prevents accurate determination of an annulus area within a particular region of an inflow nozzle component 104. That is, the surface roughness creates a situation where there is a different annular space area at any given cross section, such as those in Fig. 2 at lines A-A or B-B. The variation V can e.g. up to 1.3 centimeters. Variation V complicates accurate calculations of pressure and / or mass flow because of the difficulty of determining an accurate annular area area required to calculate the pressure and / or mass flow. Although the term "annulus" is used to refer to a particular cross-sectional area, it will be understood that the inlet nozzle component 104 need not have an exactly circular cross-section such that it is e.g. may be oblong, polygonal or oval. The substantially uneven surface 120 may be created in several ways. However, one illustrative reason for this is that the inlet nozzle component 104 is formed by pouring e.g. Iron, steel, etc. is produced. The substantially uneven surface 120 is present in the manufacture of the inflow nozzle component 104 and may change as an airflow 114 abrades it over time due to its initial rough nature. Although the airflow 114 may rub against the surface 120, the airflow is usually not such that it would smooth the surface 120 in an acceptable manner.
    Returning to FIG. 1, to address the substantially uneven surface 120, a coating 102 of varying thickness is selectively created in a measuring annulus area 130 of the substantially uneven inner surface 102. The coating 102 is not present on all surfaces of the inlet nozzle component 104, but only in the measuring annulus area 130. The measuring annulus area 130 may include any annulus area where static pressure of the air flow 114 through the inlet nozzle component 104 is measured. While the measuring annulus area 130 in Figure 1 (and Figure 6) is illustrated as being substantially cylindrical, as described, this arrangement is not necessary in all cases. For example, as will be described in greater detail, struts 150 may be present within and form part of the gauge ring space 130. Understandably, the struts 150 serve to support an outer portion 152 of the inlet nozzle component 104 with respect to its inner portion 154.
    As shown in FIG. 3, the coating 102 of varying thickness is configured to provide a richer inner surface 132 than the substantially uneven surface 120. For example, a variation of the planar surface 132 may be up to 0.2 centimeters, which greatly improves the accuracy of an annulus area used for pressure calculations. A coating 102 of varying thickness may contain any material capable of being fixedly connected to the substantially uneven inner surface 120, filling the variations V (FIG. 2) and the ambient of the airflow 114 (eg, a maximum temperature of eg, about 60-64 ° C, solid particles or moisture in the air flow, etc.). In one embodiment, the coating 102 is non-metallic. The coating 102 may include, but is not limited to, an epoxy, plastic or fiberglass. The coating 102 may be applied using any suitable methodology for the material used, e.g. by spraying, infusion, injection, deposition, etc. The coating 102 may have a thickness in the range of e.g. about 1.3-2.5 centimeters.
    As shown in FIGS. 1 and 6, in many situations, the static pressure sensor system 116 includes a number of sensors 118 disposed about a particular circumference of the inlet nozzle component 104. In this case, the static pressure sensor system 116 may also include a number of sensors 118 extending circumferentially along the inlet nozzle component 104, i. are arranged around the Meßringraumbereich 130 around. The sensors 118 may include any known or future developed pressure sensors. One or more sensors 118 measure static pressure only within the annulus area 130. The annulus area 130 covers a preferred annulus area of the inlet nozzle component 104, where access for the sensor (s) 118 may be easier, the airflow 114 is more laminar etc. The static pressure sensor system 116 may use any known or future developed methodology for determining static pressure, such as, but not limited to, those described in Airflow Calibration of a Bellmouth Inlet for Measurement of Compressor Airflow in US Pat Turbine-Powered Propulsion Simulators, "(" Airflow Calibration of Inlet Nozzle Inlet to Measure Compressor Airflow in Turbine Propulsion Simulators "), by Stephen A. Smith, National Aeronautics and Space Administration Technical Memorandum 84399, November 1985.
    In another embodiment, the airflow inlet 100 inflow nozzle component 104 may include a static pressure annulus area 130 configured to measure a static pressure by at least one sensor 118. The measuring annulus area 130 includes a coating 102 of varying thickness on the substantially uneven inner surface 120 of the inlet nozzle component 104 in the measuring annulus area. The coating 102 of varying thickness is configured to provide a smoother deviation of the surface 132 (see FIG. 3) than the substantially uneven inner surface 120 within the measuring annulus area. Consequently, a more accurate annular space area can be determined.
    It is emphasized that in addition to the time when the inlet nozzle component 104 is first manufactured, the coating 102 of varying thickness can be applied at multiple times throughout the life of the inlet nozzle component 104. In particular, the coating 102 of varying thickness, according to one embodiment of a method of the invention, may be applied by applying to the inlet nozzle component 104 of the airflow inlet, e.g. at the point of use and after a period of use, by removing any protective filters, shields, etc. at an open end of the inlet nozzle component 104. The coating 102 of varying thickness may be applied to a measuring annulus area 130 of a substantially uneven inner surface 120 of the inflow nozzle component 104 to create a planar inner surface 132. As mentioned herein, the application may include any method suitable for the material used, e.g. Spraying, infusion, injection, deposition, etc. If a correction factor initially based on the substantially uneven inner surface 120 is used to determine a static pressure (and / or mass flow) of air flow 114 through the inlet nozzle component 104, the correction factor to determine a static pressure based on a more planar surface 132. In the manner described above, the coating 102 of varying thickness can be applied to previously installed and used inlet nozzle components without replacement and in most cases without removal of the component.
    While Figure 1 shows a shape of the inlet nozzle component 104, it will be understood that various other shapes and arrangements are possible as can be observed in Figures 4-5. For example, an inlet nozzle component may be more or less rounded, longer or shorter, or have more straight or curved sides, etc. In FIG. 4, a trumpet shaped inflow nozzle component 204 having a measuring annulus area 230 is substantially longer and has more arcuate sides than the inlet nozzle component 104 in FIG 1, and in FIG. 5, a trumpet-shaped inflow nozzle component 304 having a measuring annulus area 330 has substantially aligned or parallel sides. In addition, a measuring annulus does not have to be substantially cylindrical as in FIG. For example, as shown in FIG. 5, a measuring annulus region 330 may include opposing beveled sides 334, and FIG. 4 illustrates a gage annulus region 230 having a neck region 234 that has a slightly smaller diameter than adjacent regions. In addition, FIG. 6 shows an end view of one embodiment of the inlet nozzle component 204, as in FIG. 4, containing a coating 102 on one or more of its struts 150. As shown in FIGS. 4 and 6, the annulus or gauge annulus portion 230 includes at least one strut 150 that is at least partially covered by the coating 102 of varying thickness.
    While the use of a coating 102 of varying thickness has been described herein as one that makes the inlet nozzle component 104 uniform in size for the purposes of measuring static pressure, it will be understood that the coating 102 may act to accommodate other measurements which allows more accurate control of any industrial component based on the particular measurement.
    The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the disclosure. As used herein, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly dictates otherwise. It will further be understood that the terms "comprising" and / or "having" when used in this specification describe the presence of the specified features, integers, steps, operations, elements and / or components, but the presence or adding one or more further features, integers, steps, operations, elements, components and / or groups thereof.
    The corresponding structures, materials, acts, and equivalents of all means or steps plus function elements in the appended claims are intended to cover any structure, material, or act of performing the function in combination with other claimed elements. as specifically claimed. The description of the present disclosure has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the disclosure in the form disclosed. Many modifications and variations will become apparent to those skilled in the art without departing from the scope and spirit of the disclosure. The embodiment has been chosen and described to best explain the principles of the disclosure and the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as appropriate to the use contemplated are.
    An airflow inlet may include an inlet nozzle component having a substantially uneven inner surface and a coating of varying thickness in a measuring annulus area of the substantially uneven inner surface. The measuring annulus area merely contains an annulus around the inner surface of the inlet nozzle component. The coating of varying thickness is configured to provide a smoother surface than the substantially uneven inner surface.
    LIST OF REFERENCE NUMBERS
    [0038]<Tb> 100 <September> air flow inlet<Tb> 102 <September> Coating<tb> 104, 204, 304 <SEP> Injection nozzle component<Tb> 110 <September> compressor<Tb> 112 <September> Turbine<Tb> 114 <September> airflow<tb> 116 <SEP> Static Pressure Sensor System<Tb> 118 <September> Sensors<tb> 120 <SEP> inner surface<tb> 130, 230, 330 <SEP> Annular area<Tb> 132 <September> surface<Tb> 150 <September> pursuit<tb> 152 <SEP> outer section<tb> 154 <SEP> inner section<Tb> 234 <September> neck<tb> 334 <SEP> beveled pages
    权利要求:
    Claims (10)
    [1]
    An airflow inlet comprising:an inlet nozzle component having a substantially uneven inner surface; anda coating of varying thickness in a measuring annulus area of the substantially uneven inner surface, wherein the coating of varying thickness is arranged to provide a more planar inner surface than the substantially uneven inner surface,wherein the measuring annulus area only includes an annulus around the inner surface of the inlet nozzle component.
    [2]
    2. Airflow inlet according to claim 1, wherein the coating contains at least one of epoxy, plastic and / or glass fiber.
    [3]
    3. The airflow inlet of claim 1 or 2, further comprising a static pressure sensor system configured to determine a static pressure of airflow through the inlet nozzle component using an annulus cross-sectional area based on the planar inner surface.
    [4]
    An airflow inlet according to any one of the preceding claims, wherein the inlet nozzle component includes a molded inlet nozzle component having a substantially uneven surface.
    [5]
    5. Airflow inlet according to any one of the preceding claims, wherein the substantially uneven inner surface varies by up to 1.3 centimeters.
    [6]
    An air flow inlet according to any one of the preceding claims, wherein the measuring annulus area includes opposing beveled sides.
    [7]
    An airflow inlet according to any of the preceding claims, wherein the annulus includes at least one strut which is at least partially covered by the coating of varying thickness.
    [8]
    An inlet nozzle component for an airflow inlet, the inlet nozzle component comprising:a static pressure measuring annulus area adapted to measure static pressure by at least one sensor system, the annulus space area including a coating of varying thickness on a substantially uneven inner surface of the inlet nozzle component in only the annulus space area, the varying thickness coating being adapted to to provide a more planar surface variation than the substantially uneven inner surface within the measuring annulus area.
    [9]
    9. A method comprising:Accessing an inflow nozzle component of an airflow inlet, the inflow nozzle component including a substantially uneven interior surface; andApplying a coating of varying thickness to a measuring annulus area of the substantially uneven inner surface of the inflow nozzle component to produce a more planar inner surface, the measuring annulus area containing only an annulus around the inner surface of the inflow nozzle component.
    [10]
    10. The method of claim 9, further comprising checking a correction factor used to determine a static pressure of an air flow through the inlet nozzle component, wherein the correction factor is initially based on the substantially uneven inner surface.
    类似技术:
    公开号 | 公开日 | 专利标题
    DE2512644C3|1979-10-18|Device for determining the flow rate and / or the viscosity of a fluid
    DE60018728T2|2006-04-13|SOLID MULTIFUNCTION PROBE FOR AIRCRAFT
    CH710050A2|2016-02-29|Intake airflow with an inlet nozzle with a coating in a measuring annulus region.
    DE102014014398A1|2016-04-07|Fluid management system
    AT512619A2|2013-09-15|Flowmeter
    DE2530357C2|1982-06-16|Device for displaying icing on aircraft
    EP2041523B1|2010-05-19|Measuring arrangement for flow measurement in a channel
    DE102015119090A1|2016-05-12|Pressure sensor system for calculating a mass flow of a compressor using sensors at an antechamber and a compressor entry level
    DE112013001966T5|2015-01-15|turbocharger
    DE102015001826B3|2016-03-31|fitting
    DE3153462C2|1991-05-02|
    DE102012021363A1|2014-05-22|Method for determining the flow according to the float principle and corresponding device
    EP3109603B1|2019-01-02|Method for operating a flow meter and flow meter
    DE112020001927T5|2022-01-13|FLOW METER
    DE102018204415A1|2019-09-26|sensor arrangement
    DE102012023861A1|2014-06-12|Device for determining the flow according to the float principle
    DE4134589A1|1993-04-22|METHOD FOR DIAGNOSIS OF WEARING MACHINE PARTS
    DE102014220522B4|2016-09-15|Determination of a corrected pressure signal
    DE202011105181U1|2011-12-22|Test bench for the investigation of the wear behavior on cylinder inner surfaces
    DE112018002008T5|2020-01-09|Air flow measuring device
    EP3388639A2|2018-10-17|Measuring device and measuring method for a flow
    DE102015201817A1|2016-08-04|Mass flow CNG valve
    DE102017129446A1|2019-06-13|Device for determining a total pressure loss of a radiator of a motor vehicle
    DE102015218488A1|2016-12-22|Volumetric structure for a cylinder head and a piston for a motor
    DE202019003182U1|2019-08-14|Area marker for display devices
    同族专利:
    公开号 | 公开日
    DE102015113147A1|2016-02-25|
    JP2016044678A|2016-04-04|
    CN105386999A|2016-03-09|
    US20160053767A1|2016-02-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6220234B1|1999-03-04|2001-04-24|Cummins Engine Company|Coated compressor diffuser|
    KR100625731B1|2002-01-23|2006-09-21|캐리어 코포레이션|Method to rough size coated components for easy assembly|
    US9043118B2|2007-04-02|2015-05-26|General Electric Company|Methods and systems for model-based control of gas turbines|
    US7962307B2|2009-02-23|2011-06-14|General Electric Company|Integrated apparatus for measuring static pressure|
    US8639480B2|2010-09-20|2014-01-28|General Electric Company|Methods and systems for modeling turbine operation|
    US9784134B2|2013-09-25|2017-10-10|Pratt & Whitney Canada Corp.|Gas turbine engine inlet assembly and method of making same|
    US20160131146A1|2014-11-07|2016-05-12|General Electric Company|Pressure sensor system for calculating compressor mass flow rate using sensors at plenum and compressor entrance plane|DE102016115616A1|2016-08-23|2018-03-01|Ebm-Papst Mulfingen Gmbh & Co. Kg|Flow straightener of a fan|
    FR3069291B1|2017-07-24|2019-12-13|Safran Aircraft Engines|SUPPLY DUCT FOR A COMPRESSOR OF A TURBOMACHINE|
    CN110966056B|2019-12-30|2022-02-15|中国科学院工程热物理研究所|Method and structure for reducing friction loss of wall surface of compressed air energy storage turbine gas collection chamber|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-11-30| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/465,148|US20160053767A1|2014-08-21|2014-08-21|Inlet bellmouth with coating in measurement annulus region|
    [返回顶部]