GB2467154A - Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner - Google Patents

Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner Download PDF

Info

Publication number
GB2467154A
GB2467154A GB0901141A GB0901141A GB2467154A GB 2467154 A GB2467154 A GB 2467154A GB 0901141 A GB0901141 A GB 0901141A GB 0901141 A GB0901141 A GB 0901141A GB 2467154 A GB2467154 A GB 2467154A
Authority
GB
United Kingdom
Prior art keywords
coolant
fan
plenum
supply
test rig
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Withdrawn
Application number
GB0901141A
Other versions
GB0901141D0 (en
Inventor
Thibault Roland Christophe Maurice Pringuey
David Steele
John Charles Williams
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB0901141A priority Critical patent/GB2467154A/en
Publication of GB0901141D0 publication Critical patent/GB0901141D0/en
Publication of GB2467154A publication Critical patent/GB2467154A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K17/00—Measuring quantity of heat
    • G01K17/06—Measuring quantity of heat conveyed by flowing media, e.g. in heating systems e.g. the quantity of heat in a transporting medium, delivered to or consumed in an expenditure device
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/02—Details or accessories of testing apparatus
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/205—Cooling fluid recirculation, i.e. after having cooled one or more components the cooling fluid is recovered and used elsewhere for other purposes
    • 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
    • F05D2220/00—Application
    • F05D2220/20—Application within closed fluid conduits, e.g. pipes
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

A test rig and method for modelling heat transfer conditions in a film-cooled jet pipe liner or other film cooled components, comprising: a sample section of liner 3 having a plurality of film-cooling holes 3a; a fluid supply 1 for supplying a relatively hot flow of fluid 2 along a nominal hot side of the liner section 3; and a coolant delivery circuit 4 for delivering a coolant flow along a nominal cold side of the liner section 3; wherein the coolant delivery circuit 4 comprises: a supply of coolant 6; an axial fan 7 having an intake 7a fluidly connected to the coolant supply 6; and a plenum 5 enclosing the cold side of the liner around the plurality of the film cooling holes; the plenum having an inlet 5a fluidly connected to the discharge outlet 7b of the fan for receiving a discharge flow of coolant from the fan 7, and having an outlet 5b fluidly connected to an intake 7c on the fan 7 for re-circulating coolant through the fan 7. The method may comprise determining the mass flow rate of coolant leaving the coolant delivery circuit 4 through the film cooling holes 3a and using the coolant supply to inject a compensatory mass flow rate of coolant into the respective intake on the axial fan. The method may comprise variably controlling the velocity of the coolant through the plenum by adjusting the fan speed thereby controlling the heat transfer conditions for the sample component section.

Description

A TEST RIG
The present invention relates to a test rig for modelling heat transfer conditions in a film-cooled component, such as a jet-pipe liner.
A jet pipe may contain hot fluids, for example from an associated combustion process.
In the case of gas turbine engines, such jet pipes may include a flame tube in a combustor or a jet pipe forming part of a reheat system for "afterburning".
The temperature of the hot gases inside these jet pipes may be extremely high (typically peaking in excess of 200000 in the case of a combustor flame tube, for example). The jet pipes are therefore typically provided with an internal liner which protects the walls of the jet pipe from radiative and convective thermal loading by the hot main-stream fluid inside the jet pipe.
In order to increase cooling performance, the liner is typically provided spaced inwardly from the wall of the jet pipe to define a cooling passage between the liner and the jet pipe for receiving a cooling flow of relatively cold fluid (typically gas at around 700°C in the case of a combustor flame tube). The liner may also be provided with effusion holes allowing passage of cold fluid from the cooling passage through to the interior surface of the liner for "film-cooling" the interior surface of the liner.
During a development programme, test rigs may be used to model heat transfer conditions in a jet-pipe liner for performance evaluation prior to in-engine testing.
Such a test rig will generally provide a supply of relatively hot gas to a nominal hot side of a sample section of liner, representing the main-stream fluid through a jet pipe, and a supply of coolant to a nominal cold side of the section of liner, representing the relatively cold fluid passing through the cooling passage between a liner and the jet-pipe.
The coolant is typically pressure-fed into a closed plenum enclosing the nominal cold side of the sample liner section, but this method has been found to have drawbacks. In particular, it is difficult to control the velocity of the coolant in the axial direction (nominally along the cooling passage in between the jet pipe wall and the liner) and as a result convective heat transfer coefficients cannot accurately be evaluated. In addition, it has been found that where the liner sample contains effusion holes, pressure-feeding the coolant in the manner described can result in discrepancies between the discharge coefficient (Cd) for the effusion holes in the test rig and the corresponding discharge coefficient "in-engine" for the same nominal mainstream jet flow. These discrepancies undermine accurate modelling and evaluation.
It is an object of the present invention to seek to provide an improved test rig for modelling heat transfer conditions in a film-cooled jet pipe liner.
According to the present invention there is provided a test rig for modelling heat transfer conditions in a film-cooled component, comprising: a sample section of the component having a plurality of film-cooling holes; a fluid supply for supplying a relatively hot flow of fluid along a nominal hot side of the component section; and a coolant delivery circuit for delivering a coolant flow along a nominal cold side of the component section; wherein the coolant delivery circuit comprises: a supply of coolant; a fan having an intake fluidly connected to the coolant supply; and a plenum enclosing the cold side of the component section around the plurality of the film cooling holes; the plenum having an inlet fluidly connected to the discharge outlet of the fan for receiving a discharge flow of coolant from the fan, and having an outlet fluidly connected to an intake on the fan for re-circulating coolant through the fan.
The coolant delivery circuit is intended to provide better control over the velocity of coolant through the plenum, and to better approximate the corresponding discharge coefficients and mass flow rates through the effusion holes for a given velocity through the plenum.
The fan may be an axial fan.
The film-cooling holes may be angled effusion holes.
The plenum inlet and plenum outlet may be at axial ends of the plenum.
A flow conditioner is provided in the region of the plenum inlet for adjusting the flow profile of the coolant entering the plenum.
The supply of coolant may be an adjustable supply of coolant.
In one embodiment, the test rig further comprises one or more sensors for determining the mass flow of coolant leaving the coolant delivery circuit through the film-cooling holes, and a supply control unit operably responsive to the sensor or sensors for automatically adjusting the supply of coolant into the coolant delivery circuit in accordance with said mass flow determination.
The fan may be a variable drive fan having an adjustable fan speed for controlling the velocity of the coolant flow inside the plenum.
The fluid connections between the fan and the plenum may optionally be via one or more flexible hoses.
In practice, the fan may be positioned below the plenum.
According to another aspect of the present invention there is provided a method of modelling heat transfer conditions in a film-cooled component using the test rig of the present invention, the method comprising using the supply of coolant to supply coolant to the respective intake on the fan, using the fan to drive said coolant through the plenum inlet and along the cold side of the component section inside the plenum, and re-circulating coolant through the fan after the coolant has exited through the plenum outlet.
The method may include determining the mass flow rate of coolant leaving the coolant delivery circuit through the film cooling holes inside the plenum and using the coolant supply to supply a corresponding compensatory mass flow rate of coolant into the respective intake on the fan. The mass flow determination may be repeated at intervals during a test period.
The velocity of the coolant through the plenum may be adjusted by adjusting the fan speed of the axial fan, thereby to control the heat transfer conditions for the sample liner section.
The coolant and/or the hot fluid may be compressible fluids.
Embodiments of the invention will now be described, by way of example, with reference to the accompanying drawings, in which: Figure 1 is a highly schematic representation of part of a test rig for modelling heat transfer conditions in a film-cooled jet pipe liner using a sample liner section; and Figure 2 is a schematic illustrating an arrangement for controlling delivery of coolant to a nominal cold side of the sample liner section shown in Figure 1.
Referring to Figure 1, a film-cooled component in the form of a jet-pipe liner is represented in the test rig by a sample section of liner 3 having a plurality of angled effusion holes 3a for film-cooling.
A conventional fluid supply 1 is provided for supplying a relatively hot flow of fluid 2 along a nominal "hot" side of the liner section 3, representing the nominal mainstream hot fluid flow through a jet pipe, and a coolant delivery circuit 4 is provided for delivering a coolant to a nominal "cold" side of the liner section 3, representative of a cold flow through a cooling passage between the liner section 3 and a wall of a jet pipe.
The hot fluid and/or the coolant may be a compressible fluid.
The coolant delivery circuit 4 comprises a plenum 5 which encloses the cold side of the liner section 3 extending around the effusion holes 3a, a conventional supply of coolant 6, and an axial fan 7. The axial fan 7 has an intake 7a connected to the coolant supply 6 and a discharge outlet 7b fluidly connected to an inlet 5a in the plenum 5 via a flexible hose 8.
In operation, coolant is supplied by the supply 6 to the intake 7a on the fan 7, and the fan 7 is operated to drive a mass flow of coolant out through the discharge outlet 7b, through the hose 8 and into the plenum 5. The coolant enters the plenum 5 via the inlet 5a, and then flows axially along the nominal cold side of the liner section 3 towards an outlet Sb in the plenum S located at an opposite axial end of the plenum 5 from the inlet 5a.
It is intended that the axial fan 6 will drive coolant through the plenum 5 at a controlled axial velocity, allowing better simulation of cooling hole crossflow and cold-side convective heat transfer coefficients.
As the coolant flows axially along the plenum 5, a mass flow of coolant passes through the effusion holes 3a (indicated by the respective arrows in Figure 1), thereby film-cooling the "hot" surface of the liner section 3.
For typical axial velocities inside the plenum 5, the corresponding mass flow of coolant MIN entering the inlet 5a will tend to be much greater than the mass flow of coolant MFILM through the effusion holes 3a. Consequently, a net mass flow of coolant MNET will generally pass through the plenum outlet 5b.
Accurate modelling of the heat transfer characteristics for a jet-pipe liner typically requires use of a dense coolant gas. These dense "foreign" gases tend to be very expensive and/or environmentally unfriendly. Therefore, in order to prevent the mass flow of coolant MNET from being lost from the coolant delivery circuit 4, the outlet 5b on the plenum 5 is fluidly connected to an intake 7c on the fan 7 by a flexible hose 9 or other device for re-circulation of the coolant through the coolant delivery circuit 4 in the direction indicated by the arrows A and B in Figure 1. Although the fan 7 is shown comprising two separate intakes 7a and 7c, any other suitable intake configuration may be used, including a common intake for both coolant from the supply 6 and the re-circulated coolant (which may be mixed with one another upstream of the fan intake).
A velocity profile may be introduced in-between the fan 7 and the inlet 5a, for example due to the geometry of the hose. In order to modify this flow profile to a more desirable profile, a suitable flow conditioner 12 is provided at the inlet 5a of the plenum 5.
The coolant supply 6 may be an adjustable supply for controlling injection of coolant into the coolant delivery circuit 4 thereby to enhance the parametric control capability of the test rig.
Figure 2 shows a schematic control layout which may be used automatically to adjust the mass flow rate supplied by an adjustable coolant supply 6 according to a determination of the mass flow re-circulation through the coolant delivery circuit 4.
A sensor arrangement 10 is provided for determining the mass flow rate of coolant MCOOLANT ( = MFILM). The sensor arrangement 10 is operably connected to a supply control unit 11 for automatically adjusting the mass flow rate MCOOLANT supplied by the supply 6 in accordance with the determination of MFILM.
In the case where it is desired to maintain a substantially constant velocity at the inlet 5a, a determination of the coolant cold-side velocity V000LANT and corresponding adjustment of the fan speed and hence coolant flow rate MIN at the inlet 5a, may be carried out at intervals during a given test period, which intervals may vary according to the particular phase of the test period. For example, the intervals may be relatively short on "start-up" prior to initially reaching a steady state condition, but then may be relatively infrequent once a steady state mass flow rate has initially been reached at the inlet 5a.
The fan may be fixed drive (for driving coolant at a fixed, controlled velocity through the plenum 5) or variable drive, in which case the fan speed may be varied to control the axial velocity of the coolant through the plenum 5, enhancing the parametric control capability of the test rig. Control of the fan may be automated in response to a control signal and/or one or more sensor inputs.
Although the invention has been described in the context of modelling heat transfer conditions in a jet-pipe liner, the invention may in general be used for modelling heat transfer conditions in other film-cooled components provided that a suitable sample of section of the component is used.

Claims (14)

  1. CLAIMSA test rig for modelling heat transfer conditions in a film-cooled component, comprising: a sample section of the component (3) having a plurality of film-cooling holes (3a); a fluid supply (1) for supplying a relatively hot flow of fluid (2) along a nominal hot side of the component section (3); and a coolant delivery circuit (4) for delivering a coolant flow along a nominal cold side of the component section (3); wherein the coolant delivery circuit (4) comprises: a supply of coolant (6); a fan (7) having an intake (7a) fluidly connected to the coolant supply (6); and a plenum (5) enclosing the cold side of the component section around the plurality of the film cooling holes; the plenum having an inlet (5a) fluidly connected to the discharge outlet (7b) of the fan for receiving a discharge flow of coolant from the fan (7), and having an outlet (5b) fluidly connected to an intake (7c) on the fan (7) for re-circulating coolant through the fan (7).
  2. 2 A test rig according to claim 1, wherein the plenum inlet (5a) and plenum outlet (Sb) are at axial ends of the plenum (5).
  3. 3 A test rig according to claim 1 or 2, wherein a flow conditioner (12) is provided in the region of the plenum inlet (Sa) for modifying the flow profile of the coolant entering the plenum (5).
  4. 4 A test rig according to any preceding claim, wherein the supply of coolant (6) is an adjustable supply.
  5. A test rig according to claim 3, wherein the test rig further comprises one or more sensors (10) for determining the mass flow of coolant (MCOOLANT,MFILM) leaving the coolant delivery circuit through the film-cooling holes (3a), and a supply control unit operably responsive to the sensor or sensors for automatically adjusting the mass flow rate of coolant (MCOOLANT) supplied into the coolant delivery circuit (4) in accordance with said mass flow determination.
  6. 6 A test rig according to any preceding claim wherein the fan (7) has an adjustable fan speed for controlling the velocity of the coolant flow inside the plenum (5).
  7. 7 A test rig according to any preceding claim, wherein the fluid connections between the fan (7) and the plenum (5) are via one or more flexible hoses (8).
  8. 8 A test rig according to claim 6, wherein the fan (7) is positioned underneath the plenum (5).
  9. 9 A method of modelling heat transfer conditions in a film-cooled component using the test rig according to any preceding claim, the method comprising using the supply of coolant (6) to supply coolant into the respective intake (7a) on the fan (7), using the fan (7) to drive said coolant through the plenum inlet (5a) and along the cold side of the component section (3) inside the plenum (5), and re-circulating coolant through the fan (7) after the coolant has exited through the plenum outlet (5b).
  10. A method according to claim 10, comprising determining the mass flow rate (MFILM) of coolant leaving the coolant delivery circuit (4) through the film cooling holes (3a) inside the plenum (5) and using the coolant supply (6) to inject a compensatory mass flow rate of coolant (MCOOLANT) into the respective intake on the axial fan.
  11. 11 A method according to claim 10, wherein said mass flow determination is repeated at intervals during a test period.
  12. 12 A method according to any of claims 9 to 11, comprising variably controlling the velocity of the coolant through the plenum (5) by adjusting the fan speed of the fan (7) thereby to control the heat transfer conditions for the sample component section (3).
  13. 13 A test rig or method according to any preceding claim, wherein the coolant and/or the hot fluid are compressible fluids.
  14. 14 A test rig or method according to any preceding claim wherein the film-cooling holes are angled effusion holes (3a).
GB0901141A 2009-01-26 2009-01-26 Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner Withdrawn GB2467154A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0901141A GB2467154A (en) 2009-01-26 2009-01-26 Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0901141A GB2467154A (en) 2009-01-26 2009-01-26 Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner

Publications (2)

Publication Number Publication Date
GB0901141D0 GB0901141D0 (en) 2009-03-11
GB2467154A true GB2467154A (en) 2010-07-28

Family

ID=40469000

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0901141A Withdrawn GB2467154A (en) 2009-01-26 2009-01-26 Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner

Country Status (1)

Country Link
GB (1) GB2467154A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013050442A1 (en) * 2011-10-06 2013-04-11 Schenck Rotec Gmbh Method and device for powering a turbocharger
RU2618479C1 (en) * 2016-03-11 2017-05-03 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Stand for simulation of heat exchange processes in cooled blades

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109387370B (en) * 2018-11-14 2023-12-22 中国空空导弹研究院 Direct-connection type high-altitude simulation test axial force-free air inlet system of ramjet engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040037344A1 (en) * 2002-08-23 2004-02-26 Bunker Ronald Scott Method for quantifying film hole flow rates for film-cooled parts
US20070290134A1 (en) * 2005-12-07 2007-12-20 Meyer Tool, Inc. Apparatus and Method for Analyzing Relative Outward Flow Characterizations of Fabricated Features

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040037344A1 (en) * 2002-08-23 2004-02-26 Bunker Ronald Scott Method for quantifying film hole flow rates for film-cooled parts
US20070290134A1 (en) * 2005-12-07 2007-12-20 Meyer Tool, Inc. Apparatus and Method for Analyzing Relative Outward Flow Characterizations of Fabricated Features

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"Design and Calibration of a Facility for Film Cooling Research", J.S. Porter, J.E. Sargison, A.D. Henderson, 16th Australasian Fluid Mechanics Conference, 2-7 Dec 2007, Retrieved 28 Apr 2009 from: http://eprints.utas.edu.au/4871/1/porter-afmc-07.pdf *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013050442A1 (en) * 2011-10-06 2013-04-11 Schenck Rotec Gmbh Method and device for powering a turbocharger
RU2618479C1 (en) * 2016-03-11 2017-05-03 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Stand for simulation of heat exchange processes in cooled blades

Also Published As

Publication number Publication date
GB0901141D0 (en) 2009-03-11

Similar Documents

Publication Publication Date Title
US7837429B2 (en) Predictive model based control system for heavy duty gas turbines
JP5837753B2 (en) Method and system related to fuel delivery in a combustion turbine engine
EP0563180B1 (en) Heat exchange apparatus for gas turbine fluids
EP2615275B1 (en) Coolant Supply System
US7819623B2 (en) Clearance control apparatus
US20140131027A1 (en) Heat exchange arrangement
CN103968908B (en) System and method for measuring the flow distribution in turbogenerator flow path
JP6745079B2 (en) Systems and Methods for Exhaust Heat Powered Active Clearance Control
US20150354822A1 (en) Turbine stage cooling
JP2010156537A5 (en)
EP1566524A2 (en) Turbine casing cooling arrangement
US20230092512A1 (en) Gas turbine engine with active variable turbine cooling
US11208959B2 (en) System and method for flexible fuel usage for gas turbines
US20150292409A1 (en) Gas turbine engine heat management system
CN103321750A (en) Method for operating a combined cycle power plant and plant to carry out such a method
JP2010281324A (en) Methods relating to turbine engine control and operation
US10890114B2 (en) System and method for stabilizing transcritical air-to-fuel heat exchange
GB2467154A (en) Test rig and method for modelling heat transfer conditions in a film cooled component such as a jet pipe liner
JP2017115666A (en) Gas turbine cooling system, gas turbine appliance having the same, and control device and control method of gas turbine cooling system
EP3406882A1 (en) Active bleed flow modulation
US11619141B2 (en) Lubricating oil circuit of a turbomachine, turbomachine and regulation method thereof
JP7053626B2 (en) An improved way to tune the supply circuit
CN105339603A (en) Method and device for controlling the spraying of water into the flue gas duct of a gas and steam turbine installation
US8375722B2 (en) Flow modulation method and apparatus
US11525396B2 (en) Combustor apparatus with bleed arrangement and resonator with cooling flow and method of operating combustor apparatus

Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)