US20160053767A1 - Inlet bellmouth with coating in measurement annulus region - Google Patents

Inlet bellmouth with coating in measurement annulus region Download PDF

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Publication number
US20160053767A1
US20160053767A1 US14/465,148 US201414465148A US2016053767A1 US 20160053767 A1 US20160053767 A1 US 20160053767A1 US 201414465148 A US201414465148 A US 201414465148A US 2016053767 A1 US2016053767 A1 US 2016053767A1
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US
United States
Prior art keywords
internal surface
bellmouth
component
bellmouth component
annulus region
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.)
Abandoned
Application number
US14/465,148
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English (en)
Inventor
Rex Allen Morgan
Stephen Ronald Watts
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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
Application filed by General Electric Co filed Critical General Electric Co
Priority to US14/465,148 priority Critical patent/US20160053767A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MORGAN, REX ALLEN, WATTS, STEPHEN RONALD
Priority to DE102015113147.1A priority patent/DE102015113147A1/de
Priority to JP2015159746A priority patent/JP2016044678A/ja
Priority to CH01174/15A priority patent/CH710050A2/de
Priority to CN201510516597.XA priority patent/CN105386999A/zh
Publication of US20160053767A1 publication Critical patent/US20160053767A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the disclosure relates generally to airflow inlets, and more particularly, to an airflow inlet bellmouth having a coating thereon to reduce a surface roughness thereof, and a related method.
  • Airflow inlets to industrial devices such as gas turbine compressors include a bellmouth component that acts to collect, initially compress, and direct an airflow, e.g., toward a turbine portion of the compressor.
  • static pressure is measured in the inlet bellmouth component, for example, using a Pitot method.
  • the static pressure may be used to determine a mass flow rate of air which is used to better control operation of other components, for example, controlling a firing temperature of a combustor of a gas turbine.
  • mass flow rate may be used to determine a compressor operating limit degradation.
  • inlet bellmouths are oftentimes manufactured as a cast component having significant variation and large tolerances in an internal surface thereof, i.e., they are uneven or rough. The variations and large tolerances in the inlet bellmouth diminish static pressure measurement accuracy by a static pressure sensor system, and thus hinder accurate mass flow rate calculations.
  • a sampling of inlet bellmouth(s) is/are analyzed after manufacture and a calibrated correction factor is determined and employed in the static pressure calculation for all of the inlet bellmouths.
  • a first aspect of the disclosure provides an airflow inlet, comprising: a bellmouth component having a substantially uneven internal surface; and a variable thickness coating in a measurement annulus region of the substantially uneven internal surface, the variable thickness coating configured to present a more even internal surface than the substantially uneven internal surface, wherein the measurement annulus region includes only an annulus about the internal surface of the bellmouth component.
  • a second aspect of the disclosure provides a bellmouth component for an airflow inlet, the bellmouth component comprising: a static pressure measurement annulus region configured for measuring a static pressure by at least one sensor system, the measurement annulus region including a variable thickness coating on a substantially uneven internal surface of the bellmouth component in only the measurement annulus region, the variable thickness coating configured to present a more even surface variation than the substantially uneven internal surface within the measurement annulus region.
  • a third aspect of the disclosure provides a method comprising: accessing a bellmouth component of an airflow inlet, the bellmouth component including a substantially uneven internal surface; and applying a variable thickness coating to a measurement annulus region of the substantially uneven internal surface of the bellmouth component to create a more even internal surface, wherein the measurement annulus region includes only an annulus about the internal surface of the bellmouth component.
  • FIG. 1 shows a cross-sectional view of an airflow inlet for a compressor, the airflow inlet including a coating on a measurement annulus region of the bellmouth component according to embodiments of the invention.
  • FIG. 2 shows an enlarged cross-sectional view of a substantially uneven internal surface of a bellmouth component of the airflow inlet.
  • FIG. 3 shows an enlarged cross-sectional view of an internal surface of the bellmouth component of the airflow inlet with the coating.
  • FIGS. 4 and 5 show cross-sectional views of airflow inlets having varied shaped bellmouth components and including a coating on a measurement annulus region according to embodiments of the invention.
  • FIG. 6 shows an end view of one embodiment of a bellmouth component including a coating on struts thereof according to embodiments of the invention.
  • FIG. 1 a cross-sectional view of an airflow inlet 100 including a variable thickness coating 102 on a bellmouth component 104 according to embodiments of the invention is illustrated.
  • the illustrative setting for airflow inlet 100 includes a compressor 110 for, e.g., a gas turbine.
  • Compressor 110 includes a turbine (or turbo-fan) 112 for drawing an airflow 114 into bellmouth component 104 .
  • Bellmouth component 104 may include any structure through which airflow initially passes as part of an intake.
  • a bellmouth 104 acts to collect airflow 114 , and direct it to turbine 112 in which extensive compression occurs prior to the airflow being passed to other components (not shown).
  • Bellmouth component 104 may be referred to by various alternative names such as: intake, compressor intake, bellmouth, flow nozzle, etc.
  • a static pressure sensor system 116 may be provided that is configured to determine a static pressure of airflow 114 through bellmouth component 104 in a measurement annulus or band region 130 .
  • Other control systems may employ the pressure measurement to determine a mass flow rate through airflow inlet 100 and/or control other components.
  • FIG. 2 shows an enlarged cross-sectional view of bellmouth component 104 without a coating as taught herein.
  • bellmouth component 104 exhibits a substantially uneven internal surface 120 having a large amount of surface variation V.
  • substantially uneven internal surface indicates a non-smooth or rough surface that generally prevents an accurate determination of an annulus area within a particular region of bellmouth component 104 . That is, the surface roughness creates a situation in which at any given cross-section, such as those at lines A-A or B-B in FIG. 2 , a different annulus area is presented.
  • Variation V may be, for example, up to 1.3 centimeters.
  • Variation V makes accurate pressure and/or mass flow rate calculations difficult because an accurate annulus area, required for calculating the pressure and/or mass flow rate, is difficult to ascertain.
  • annulus has been used to denote a particular cross-sectional area, it is understood that bellmouth component 104 may not have an exactly circular cross-section, e.g., it can be oblong, polygonal or oval in cross-section.
  • Substantially uneven surface 120 can be created in a number of ways.
  • One illustrative cause, however, is that bellmouth component 104 is created by casting, e.g., iron, steel, etc.
  • Substantially uneven surface 120 is present at manufacture of bellmouth component 104 , and may change as airflow 114 wears on it over time due to its initially rough nature. Although airflow 114 may wear on surface 120 , the airflow typically does not act to smooth surface 120 in an acceptable manner.
  • a variable thickness coating 102 is selectively provided in a measurement annulus region 130 of substantially uneven internal surface 102 .
  • Coating 102 is not present on all surfaces of bellmouth component 104 , but only in measurement annulus region 130 .
  • Measurement annulus region 130 may include any annulus area at which a static pressure of airflow 114 through bellmouth component 104 is measured. While measurement annulus region 130 is illustrated in FIG. 1 (and FIG. 6 ) as being substantially cylindrical, as will be described, this arrangement is not necessary in all cases.
  • struts 150 may be present within and form part of measurement annulus region 130 . As understood, struts 150 act to support an outer portion 152 of bellmouth component 104 relative to an inner portion 154 thereof.
  • variable thickness coating 102 is configured to present a more even internal surface 132 than substantially uneven internal surface 120 .
  • a variation of more even internal surface 132 may be, for example, up to 0.2 centimeters, which greatly improves the accuracy of an annulus area used for pressure calculations.
  • Variable thickness coating 102 may include any material capable of fixed coupling with substantially uneven internal surface 120 , filling variations V ( FIG. 2 ) and withstanding the environment of airflow 114 (e.g., maximum temperature such as about 60-64° C., particulate or moisture in the airflow, etc.).
  • coating 102 is non-metallic.
  • Coating 102 may include but is not limited to: an epoxy, a plastic or a fiberglass. Coating 102 may be applied using any appropriate method for the material used, e.g., spraying, infusion, injection, deposition, etc. Coating 102 may have a thickness, for example, in the range of approximately 1.3-2.5 centimeters.
  • static pressure sensor system 116 includes a number of sensors 118 positioned about a particular circumference of bellmouth component 104 .
  • static pressure sensor system 116 may also include a number of sensors 118 circumferentially positioned along bellmouth component 104 , i.e., about measurement annulus region 130 .
  • Sensors 118 may include any now known or later developed pressure sensors.
  • One or more sensors 118 measure static pressure only within measurement annulus region 130 .
  • Annulus region 130 covers a preferred annulus area of bellmouth component 104 where access may be easier for sensor(s) 118 , airflow 114 is more laminar, etc.
  • Static pressure sensor system 116 may use any now known or later developed methodology to determine the static pressure such as but not limited to that described in “Airflow Calibration of a Bellmouth Inlet for Measurement of Compressor Airflow in Turbine-Powered Propulsion Simulators,” Stephen A. Smith, National Aeronautics and Space Administration Technical Memorandum 84399, November 1985.
  • bellmouth component 104 for airflow inlet 100 may include a static pressure measurement annulus region 130 configured for measuring a static pressure by at least one sensor 118 .
  • Measurement annulus region 130 includes variable thickness coating 102 on substantially uneven internal surface 120 of the bellmouth component 104 in the measurement annulus region.
  • Variable thickness coating 102 is configured to present a more even surface 132 variation (see FIG. 3 ) than substantially uneven internal surface 120 within the measurement annulus region. Consequently, a more accurate annulus area can be ascertained.
  • variable thickness coating 102 may be applied at a variety of points in time across the life of bellmouth component 104 .
  • variable thickness coating 102 may be applied, according to an embodiment of a method of the invention, by accessing bellmouth component 104 of an airflow inlet, e.g., in the field and after some time of use by removing any protective filters, shielding, etc., at an open end of bellmouth component 104 .
  • Variable thickness coating 102 may be applied to measurement annulus region 130 of substantially uneven internal surface 120 of bellmouth component 104 to create a more even internal surface 132 .
  • the applying may include any appropriate method for the material used, e.g., spraying, infusion, injection, deposition, etc.
  • a correction factor is employed that is initially based on substantially uneven internal surface 120 to determine a static pressure (and/or a mass flow rate) of airflow 114 through bellmouth component 104
  • the correction factor can be revised for determining a static pressure based on more even surface 132 .
  • variable thickness coating 102 can be applied to previously installed and used bellmouth components without replacement and, in most cases, without removal of the component.
  • FIG. 1 shows one form of bellmouth component 104 , as observed in FIGS. 4-5 , it is understood that various other shapes and arrangements are possible.
  • a bellmouth component may be more or less rounded overall, longer or shorter, or have straighter or curvier sides, etc.
  • a bellmouth component 204 with measurement annulus region 230 is generally longer and has more curved sides than bellmouth component 104 in FIG. 1
  • a bellmouth component 304 with measurement annulus region 330 has substantially aligned or parallel sides.
  • a measurement annulus region need not be substantially cylindrical as in FIG. 1 .
  • FIG. 1 shows one form of bellmouth component 104 , as observed in FIGS. 4-5 , it is understood that various other shapes and arrangements are possible.
  • a bellmouth component may be more or less rounded overall, longer or shorter, or have straighter or curvier sides, etc.
  • a bellmouth component 204 with measurement annulus region 230 is generally longer and has more curved sides than bellmouth component 104 in FIG. 1
  • a measurement annulus region 330 may have opposing slanted sides 334
  • FIG. 4 shows measurement annulus region 230 with a throat region 234 that has a slightly smaller diameter than adjacent regions.
  • FIG. 6 shows an end view of one embodiment of bellmouth component 204 , as in FIG. 4 , including coating 102 on one or more struts 150 thereof.
  • the annulus or measurement annulus region 230 includes at least one strut 150 at least partially covered with variable thickness coating 102 .
  • variable thickness coating 102 has been described herein as making bellmouth component 104 dimensionally consistent for the purposes of measuring static pressure, it is understood that coating 102 may act to improve other measurements, thus allowing more accurate control of any industrial component that relies on the particular measurement.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Volume Flow (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
US14/465,148 2014-08-21 2014-08-21 Inlet bellmouth with coating in measurement annulus region Abandoned US20160053767A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US14/465,148 US20160053767A1 (en) 2014-08-21 2014-08-21 Inlet bellmouth with coating in measurement annulus region
DE102015113147.1A DE102015113147A1 (de) 2014-08-21 2015-08-10 Einströmdüse mit einer Beschichtung in einem Messringraumbereich
JP2015159746A JP2016044678A (ja) 2014-08-21 2015-08-13 計測アニュラス領域におけるコーティングを有する入口ベルマウス
CH01174/15A CH710050A2 (de) 2014-08-21 2015-08-14 Luftstromeinlass mit einer Einströmdüse mit einer Beschichtung in einem Messringraumbereich.
CN201510516597.XA CN105386999A (zh) 2014-08-21 2015-08-21 在测量环带区域中具有涂层的进口喇叭口

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/465,148 US20160053767A1 (en) 2014-08-21 2014-08-21 Inlet bellmouth with coating in measurement annulus region

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US20160053767A1 true US20160053767A1 (en) 2016-02-25

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US14/465,148 Abandoned US20160053767A1 (en) 2014-08-21 2014-08-21 Inlet bellmouth with coating in measurement annulus region

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US (1) US20160053767A1 (de)
JP (1) JP2016044678A (de)
CN (1) CN105386999A (de)
CH (1) CH710050A2 (de)
DE (1) DE102015113147A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180058459A1 (en) * 2016-08-23 2018-03-01 Ebm-Papst Mulfingen Gmbh & Co. Kg Flow rectifier of a fan
US20190024586A1 (en) * 2017-07-24 2019-01-24 Safran Aircraft Engines Supply duct of a compressor of a turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110966056B (zh) * 2019-12-30 2022-02-15 中国科学院工程热物理研究所 降低压缩空气储能涡轮集气室壁面摩擦损失的方法及结构

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US6220234B1 (en) * 1999-03-04 2001-04-24 Cummins Engine Company Coated compressor diffuser
US20120072194A1 (en) * 2010-09-20 2012-03-22 General Electric Company Methods and Systems for Modeling Turbine Operation
US20150086352A1 (en) * 2013-09-25 2015-03-26 Pratt & Whitney Canada Corp. Gas Turbine Engine Inlet Assembly and Method of Making Same
US20160131146A1 (en) * 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

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Publication number Priority date Publication date Assignee Title
AU2002237937B2 (en) * 2002-01-23 2006-02-02 Carrier Corporation Method to rough size coated components for easy assembly
US9043118B2 (en) * 2007-04-02 2015-05-26 General Electric Company Methods and systems for model-based control of gas turbines
US7962307B2 (en) * 2009-02-23 2011-06-14 General Electric Company Integrated apparatus for measuring static pressure

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6220234B1 (en) * 1999-03-04 2001-04-24 Cummins Engine Company Coated compressor diffuser
US20120072194A1 (en) * 2010-09-20 2012-03-22 General Electric Company Methods and Systems for Modeling Turbine Operation
US20150086352A1 (en) * 2013-09-25 2015-03-26 Pratt & Whitney Canada Corp. Gas Turbine Engine Inlet Assembly and Method of Making Same
US20160131146A1 (en) * 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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180058459A1 (en) * 2016-08-23 2018-03-01 Ebm-Papst Mulfingen Gmbh & Co. Kg Flow rectifier of a fan
US11047394B2 (en) * 2016-08-23 2021-06-29 Ebm-Papst Mulfingen Gmbh & Co. Kg Flow rectifier of a fan
US20190024586A1 (en) * 2017-07-24 2019-01-24 Safran Aircraft Engines Supply duct of a compressor of a turbine engine
US11047303B2 (en) * 2017-07-24 2021-06-29 Safran Aircraft Engines Supply duct of a compressor of a turbine engine

Also Published As

Publication number Publication date
CN105386999A (zh) 2016-03-09
JP2016044678A (ja) 2016-04-04
DE102015113147A1 (de) 2016-02-25
CH710050A2 (de) 2016-02-29

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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MORGAN, REX ALLEN;WATTS, STEPHEN RONALD;REEL/FRAME:033583/0191

Effective date: 20140821

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION