US3854843A - Composite elongate member having a predetermined effective coefficient of linear expansion - Google Patents

Composite elongate member having a predetermined effective coefficient of linear expansion Download PDF

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Publication number
US3854843A
US3854843A US00309790A US30979072A US3854843A US 3854843 A US3854843 A US 3854843A US 00309790 A US00309790 A US 00309790A US 30979072 A US30979072 A US 30979072A US 3854843 A US3854843 A US 3854843A
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United States
Prior art keywords
shroud ring
stator shroud
rotor
linear expansion
stator
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Expired - Lifetime
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US00309790A
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English (en)
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R Penny
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    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • stator shroud ring assembly in which a turbine of-a gas turbine engine is positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor,the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the co-efficients of linear expansion of the materials employed and the total arcuate length employed of each material being such that the circumferential length of whole shroud ring will change with temperature by an amount corresponding to a predetermined effective co-efficient of linear expansion substantially equal to that of the rotor material.
  • the invention relates to a composite elongate member having a predetermined effective coefficient of linear expansion and is particularly, but not exclusively, concerned with a stator shroud ring assembly to be arranged concentrically around a turbine rotor of a gas turbine engine.
  • a stator shroud ring is provided around the periphery of a turbine rotor to define the radially outer boundary of the working fluid passage through the turbine.
  • the blades of the rotor may themselves be unshrouded or they may be provided with a shroud integral with the blades and concentric with the stator shroud ring.
  • There must ofcourse be running clearance provided by an annular gap of a predetermined radial thickness between the tips of the blades, where they are unshrouded, and the stator shroud ring or between the rotor shroud ring, where provided, and the stator shroud ring.
  • the turbine rotor including the blades and the rotor shroud ring, where provided, is made of a material selected to withstand the necessary high working temperatures.
  • the stator shroud ring is subjected to the same working temperatures and is likewise made of a material capable of withstanding high temperature.
  • stator shroud ring will expand more than the rotor and therefore the annular gap will increase in radial thickness as working temperature increases. This is because the temperature gradient radially of the rotor increases from the hub to the blade tips or the rotor shroud ring, where provided. The increase in the radial thickness of the gap results in loss of performance when the turbine has reached its operating temperature, because there must be a minimum clearance when the turbine is cold to prevent the rotor rubbing against the stator shroud ring.
  • An object of the invention is to provide a stator shroud ring which'will have substantially the same radial expansion characteristics as the rotor, thereby resulting in an annular gap between the rotor and the stator shroud ring of substantially uniform radial thickness throughout the range'of operating temperature of the turbine.
  • a composite elongate member is constructed from at least one portion madeof one material and at least one portion made .of an-' other material, the portions being assembled end-toend and the co-efficients of linear expansion of the materials employed and the total length employed of each material being such that the whole member when subjected to a temperature change will-change in length by an amount corresponding to a predetermined effective co-efficie'nt of linear expansion,
  • the invention also provides a stator shroud ring assembly in which a turbine rotor of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud-ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled end-to-end and the co-efficients of linear expansion of efficient of linear expansion as the nickel-based alloy;
  • stator shroud ring is formed from arcuate portions of two different materials but arcuate portions made of more than two materials may be used if desired.
  • one of the materials from whichthe arcuate portions are made is the same as that from which the rotor is formed, the other material or materials having a lower co-efficient of expansion, whereby the effective expansion of thecomposite stator shroud ring will be substantially the same as that of the rotor.
  • the arcuate portions. may have interengageable end faces.
  • the arcuate portions may be bounded by a concentric enveloping ring made of a material having a co-v efficient of linear expansion substantially the same as the material from which the turbine rotor is formed.
  • the material of the concentric enveloping ring may have inferior stress rupture properties compared with the material from which the rotor is made.
  • the invention also includes a gas turbine including a rotor and a stator shroud'ring assembly inaccordance with any one of the five immediately preceding paragraphs.
  • FIG. 1 isan axial section through a peripheral portion of the turbine
  • FIG. 2 is an end view of the turbine shown in FIG. 1;
  • FIG. 3 shows a modified form of the stator shroud 'ring shown in FIG. 2, and
  • FIG. 4 is' a view similar to FIG. 1' showing a further modification.
  • the turbine has a stator shroud ring formed from a plurality of arcuate portions l, 2 two or more abutted together circumferentially to 'form a complete annulus;
  • arcuate portions 1 are made of 'two different materials but where there are more than two arcuate portions more than two materials may be used.
  • One or more of the arcuate portions 1 are made of the same material as the rotor 12, e.g.,'
  • arcuate portion or portions 2 are made of a ceramic or ceramic-like material, such as silicon nitride.
  • the arcuate portions are held within an enveloping concentric outer ring 3 which may be made of a material having the same cobut which may be made of a cheaper material having an inferior stress rupture property, which itself would not be capable of withstanding the stresses to which the stator shroud ring will be subjected during operation of the turbine.
  • the ratio of the total circumferential length of the arcuate portions 2t0 the total circumferential length of the alloy portions 1 is such that the effective co-efficient of linear expansion of the composite stator shroud ring is substantially equal to the coefficient of linear expansion of the material of the rotor.
  • the effective relative coefficient of linear expansion of the composite stator ring could also be made to be 12 by making the ratio of the circumferential lengths of the alloy to ceramic segmental portions in the ratio of 3:2.
  • the radial dimension of the gap X between the stator shroud ring and the tips of the rotor blades, or the rotor blade shroud ring, where provided, is maintained substantially constant over the range of operating temperatures for which the turbine has been designed.
  • the composite shroud ring 1, 2 may extend over a ring of nozzle guide vanes as well as the rotor blades.
  • the arcuate portions 1, 2 may have interengaging ends, such as ribs and notches 6 to maintain correct relative location of the portions.
  • each of 7 the portions may be made concave and convex respectively as shown at 7 in FIG. 3. This construction would also maintain adjacent ends of theportions at the correct radial locations.
  • FIG. 4 shows a modification of the construction I shown in FIG. 2 in which the concentric enveloping ring 8 is tapered in the axial direction and is engaged with a frusto-conical face of a housing member 9.
  • a spring 10 acts betwen the ring 8 and a second housing member 1 l and thereby urges the ring 8 by wedging ac-- tion radially inwardly against the composite: ring 1, 2.
  • the arcuate portions 1, 2 will be maintained in end-to-end abutment.
  • stator shroud ring assembly in which a turbine of a gas turbine engine is to be positioned with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ring assembly including a stator shroud ring constructed from at least one arcuate portion made of one material and at least one arcuate portion made of another material, the arcuate portions being assembled ,end-to-end and the co-efficients of linear expansion of the material employed and the total arcuate length employed of each material'being such that the circumferential length of the whole shroud ring will change with temperature, within the range of working temperature for which the engine has been designed, by an amount corresponding to a predetermined effective cO-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the afores
  • stator shroud ring assembly as claimed in claim 1 in which thestator shroud ring is formed from arcuate portions of two different materials.
  • a stator shroud ring assembly as claimed in claim 1 in which a concentric enveloping ring made of a material having a co-efiicient of linear expansion substantially the same as the material from which the turbine rotor is made bounds the arcuate portions of the stator shroud ring.
  • a gas turbine engine including a bladed turbine rotor and a stator shroud ring assembly, the latter defining a stator shroud ring surrounding the rotor with an annular gap of predetermined radial distance between the stator shroud ring and the periphery of the turbine rotor, the stator shroud ringbeing constructed from at least one arcuate portion made of one material and at least one arcuate portion madeof another material, the arcuate portions being assembled end-to-end andthe co-efficients of linearexpansion of the materials employed and the total arcuate length employed of each material being such that the circumferential responding to a predetermined effective c'o-efficient of linear expansion, whereby the total change in circumferential length of the stator shroud ring will substantially correspond to the alteration in diameter of the rotor, the radial dimension of said annular gap thereby being maintained at substantially the aforesaid predetermined value.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
US00309790A 1971-12-01 1972-11-27 Composite elongate member having a predetermined effective coefficient of linear expansion Expired - Lifetime US3854843A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5566571A GB1363897A (en) 1971-12-01 1971-12-01 Composite elongate member having a predetermined effective coeffi cient of linear expansion

Publications (1)

Publication Number Publication Date
US3854843A true US3854843A (en) 1974-12-17

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ID=10474529

Family Applications (1)

Application Number Title Priority Date Filing Date
US00309790A Expired - Lifetime US3854843A (en) 1971-12-01 1972-11-27 Composite elongate member having a predetermined effective coefficient of linear expansion

Country Status (12)

Country Link
US (1) US3854843A (sv)
JP (1) JPS5138371B2 (sv)
AU (1) AU463454B2 (sv)
BE (1) BE792224A (sv)
CA (1) CA989312A (sv)
CH (1) CH561354A5 (sv)
DE (1) DE2258480A1 (sv)
FR (1) FR2164215A5 (sv)
GB (1) GB1363897A (sv)
IT (1) IT975912B (sv)
NL (1) NL7216110A (sv)
SE (1) SE385941B (sv)

Cited By (33)

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Publication number Priority date Publication date Assignee Title
JPS52143312A (en) * 1976-05-24 1977-11-29 Hitachi Ltd Steam seal ring
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4669954A (en) * 1985-01-24 1987-06-02 Societe Europeenne De Propulsion Abradable turbine rings and turbines thus obtained
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US5388959A (en) * 1993-08-23 1995-02-14 General Electric Company Seal including a non-metallic abradable material
EP1059420A1 (fr) * 1999-06-10 2000-12-13 Snecma Moteurs Stator de compresseur à haute pression
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
US20030185674A1 (en) * 2002-03-28 2003-10-02 General Electric Company Shroud segment and assembly for a turbine engine
US20040200642A1 (en) * 2000-06-21 2004-10-14 Downie Andrew Mcpherson Drilling turbine
US20040240519A1 (en) * 2003-04-28 2004-12-02 Steve Ingistov Method for monitoring the performance of a turbine
US20060013683A1 (en) * 2004-07-15 2006-01-19 Rolls-Royce Plc. Spacer arrangement
US20060013681A1 (en) * 2004-05-17 2006-01-19 Cardarella L J Jr Turbine case reinforcement in a gas turbine jet engine
US20060059889A1 (en) * 2004-09-23 2006-03-23 Cardarella Louis J Jr Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US20070243062A1 (en) * 2006-04-14 2007-10-18 Chevrette Richard J Steam turbine variable clearance packing
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine
WO2013110792A1 (de) * 2012-01-26 2013-08-01 Alstom Technology Ltd Statorbauteil mit segmentiertem innenring für eine strömungsmaschine
US20150016946A1 (en) * 2013-02-23 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US20150097342A1 (en) * 2013-10-09 2015-04-09 Snecma Labyrinth seal and rotating machine comprising such a seal
US20160146042A1 (en) * 2013-06-28 2016-05-26 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine
US9441501B2 (en) 2009-05-05 2016-09-13 General Electric Company Turbine shell with pin support
US11008882B2 (en) * 2019-04-18 2021-05-18 Rolls-Royce North American Technologies Inc. Blade tip clearance assembly
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point
US11860069B2 (en) 2021-02-25 2024-01-02 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11905479B2 (en) 2020-02-19 2024-02-20 Marathon Petroleum Company Lp Low sulfur fuel oil blends for stability enhancement and associated methods
US11970664B2 (en) 2021-10-10 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive
US11975316B2 (en) 2019-05-09 2024-05-07 Marathon Petroleum Company Lp Methods and reforming systems for re-dispersing platinum on reforming catalyst
US12000720B2 (en) 2018-09-10 2024-06-04 Marathon Petroleum Company Lp Product inventory monitoring
US12031094B2 (en) 2021-02-25 2024-07-09 Marathon Petroleum Company Lp Assemblies and methods for enhancing fluid catalytic cracking (FCC) processes during the FCC process using spectroscopic analyzers
US12031676B2 (en) 2019-03-25 2024-07-09 Marathon Petroleum Company Lp Insulation securement system and associated methods

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986720A (en) * 1975-04-14 1976-10-19 General Electric Company Turbine shroud structure
JPS5242906U (sv) * 1975-09-22 1977-03-26
JPS52127105U (sv) * 1976-03-25 1977-09-27
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
GB2165590B (en) * 1984-10-09 1988-05-05 Rolls Royce Improvements in or relating to rotor tip clearance control devices
FR2572394B1 (fr) * 1984-10-30 1986-12-19 Snecma Procede de fabrication d'un anneau de turbine en ceramique integre a un support metallique annulaire
FR2577281B1 (fr) * 1985-02-13 1987-03-20 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre aubes mobiles et carter
GB8921003D0 (en) * 1989-09-15 1989-11-01 Rolls Royce Plc Improvements in or relating to shroud rings
CA2039756A1 (en) * 1990-05-31 1991-12-01 Larry Wayne Plemmons Stator having selectively applied thermal conductivity coating
US5332358A (en) * 1993-03-01 1994-07-26 General Electric Company Uncoupled seal support assembly
DE4309199A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Vorrichtung zur Befestigung von Wärmestausegmenten und Leitschaufeln in axialdurchströmten Turbinen
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
DE102013210876B4 (de) * 2013-06-11 2015-02-26 MTU Aero Engines AG Verbundbauteil zur thermischen Spaltsteuerung in einer Strömungsmaschine sowie dieses enthaltende Strömungsmaschine
US10815816B2 (en) * 2018-09-24 2020-10-27 General Electric Company Containment case active clearance control structure

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US2555256A (en) * 1948-04-14 1951-05-29 Nat Tube Co Pipe-line pipe
US2863634A (en) * 1954-12-16 1958-12-09 Napier & Son Ltd Shroud ring construction for turbines and compressors
FR1247283A (fr) * 1959-02-09 1960-11-25 Westinghouse Electric Corp Appareillage de turbine
US2962256A (en) * 1956-03-28 1960-11-29 Napier & Son Ltd Turbine blade shroud rings
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
US3430898A (en) * 1967-05-01 1969-03-04 Us Navy Leading edge for hypersonic vehicle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2555256A (en) * 1948-04-14 1951-05-29 Nat Tube Co Pipe-line pipe
US2863634A (en) * 1954-12-16 1958-12-09 Napier & Son Ltd Shroud ring construction for turbines and compressors
US2962256A (en) * 1956-03-28 1960-11-29 Napier & Son Ltd Turbine blade shroud rings
FR1247283A (fr) * 1959-02-09 1960-11-25 Westinghouse Electric Corp Appareillage de turbine
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
US3430898A (en) * 1967-05-01 1969-03-04 Us Navy Leading edge for hypersonic vehicle

Cited By (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS52143312A (en) * 1976-05-24 1977-11-29 Hitachi Ltd Steam seal ring
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4669954A (en) * 1985-01-24 1987-06-02 Societe Europeenne De Propulsion Abradable turbine rings and turbines thus obtained
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US5388959A (en) * 1993-08-23 1995-02-14 General Electric Company Seal including a non-metallic abradable material
US6390771B1 (en) 1999-06-10 2002-05-21 Snecma Moteurs High-pressure compressor stator
EP1059420A1 (fr) * 1999-06-10 2000-12-13 Snecma Moteurs Stator de compresseur à haute pression
FR2794816A1 (fr) * 1999-06-10 2000-12-15 Snecma Stator de compresseur a haute pression
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
US20040200642A1 (en) * 2000-06-21 2004-10-14 Downie Andrew Mcpherson Drilling turbine
US7204326B2 (en) * 2000-06-21 2007-04-17 Smith International, Inc. Drilling turbine
US20030185674A1 (en) * 2002-03-28 2003-10-02 General Electric Company Shroud segment and assembly for a turbine engine
US6733235B2 (en) * 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
US20040240519A1 (en) * 2003-04-28 2004-12-02 Steve Ingistov Method for monitoring the performance of a turbine
US7013718B2 (en) * 2003-04-28 2006-03-21 Watson Cogeneration Company Method for monitoring the performance of a turbine
US20060013681A1 (en) * 2004-05-17 2006-01-19 Cardarella L J Jr Turbine case reinforcement in a gas turbine jet engine
US20060013683A1 (en) * 2004-07-15 2006-01-19 Rolls-Royce Plc. Spacer arrangement
US7396203B2 (en) * 2004-07-15 2008-07-08 Rolls-Royce, Plc Spacer arrangement
US8454298B2 (en) 2004-09-23 2013-06-04 Carlton Forge Works Fan case reinforcement in a gas turbine jet engine
US8317456B2 (en) 2004-09-23 2012-11-27 Carlton Forge Works Fan case reinforcement in a gas turbine jet engine
US20060059889A1 (en) * 2004-09-23 2006-03-23 Cardarella Louis J Jr Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US8191254B2 (en) 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US20070243062A1 (en) * 2006-04-14 2007-10-18 Chevrette Richard J Steam turbine variable clearance packing
US7484927B2 (en) * 2006-04-14 2009-02-03 General Electric Company Steam turbine variable clearance packing
US7686569B2 (en) * 2006-12-04 2010-03-30 Siemens Energy, Inc. Blade clearance system for a turbine engine
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine
US9441501B2 (en) 2009-05-05 2016-09-13 General Electric Company Turbine shell with pin support
WO2013110792A1 (de) * 2012-01-26 2013-08-01 Alstom Technology Ltd Statorbauteil mit segmentiertem innenring für eine strömungsmaschine
CN104066934A (zh) * 2012-01-26 2014-09-24 阿尔斯通技术有限公司 用于涡轮机的具有分段式内部环的定子构件
US9702262B2 (en) 2012-01-26 2017-07-11 Ansaldo Energia Ip Uk Limited Stator component with segmented inner ring for a turbomachine
US9587507B2 (en) * 2013-02-23 2017-03-07 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US20150016946A1 (en) * 2013-02-23 2015-01-15 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US20160146042A1 (en) * 2013-06-28 2016-05-26 Siemens Aktiengesellschaft Gas turbine and heat shield for a gas turbine
GB2520818B (en) * 2013-10-09 2020-01-29 Snecma Labyrinth seal and rotating machine comprising such a seal
US20150097342A1 (en) * 2013-10-09 2015-04-09 Snecma Labyrinth seal and rotating machine comprising such a seal
US9551233B2 (en) * 2013-10-09 2017-01-24 Snecma Labyrinth seal and rotating machine comprising such a seal
US11891581B2 (en) 2017-09-29 2024-02-06 Marathon Petroleum Company Lp Tower bottoms coke catching device
US12000720B2 (en) 2018-09-10 2024-06-04 Marathon Petroleum Company Lp Product inventory monitoring
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US11008882B2 (en) * 2019-04-18 2021-05-18 Rolls-Royce North American Technologies Inc. Blade tip clearance assembly
US11975316B2 (en) 2019-05-09 2024-05-07 Marathon Petroleum Company Lp Methods and reforming systems for re-dispersing platinum on reforming catalyst
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US11905468B2 (en) 2021-02-25 2024-02-20 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11898109B2 (en) 2021-02-25 2024-02-13 Marathon Petroleum Company Lp Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers
US11885739B2 (en) 2021-02-25 2024-01-30 Marathon Petroleum Company Lp Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers
US12031094B2 (en) 2021-02-25 2024-07-09 Marathon Petroleum Company Lp Assemblies and methods for enhancing fluid catalytic cracking (FCC) processes during the FCC process using spectroscopic analyzers
US11970664B2 (en) 2021-10-10 2024-04-30 Marathon Petroleum Company Lp Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive
US11802257B2 (en) 2022-01-31 2023-10-31 Marathon Petroleum Company Lp Systems and methods for reducing rendered fats pour point

Also Published As

Publication number Publication date
FR2164215A5 (sv) 1973-07-27
IT975912B (it) 1974-08-10
NL7216110A (sv) 1973-06-05
CA989312A (en) 1976-05-18
AU4931272A (en) 1974-06-06
AU463454B2 (en) 1975-07-24
DE2258480A1 (de) 1973-06-07
GB1363897A (en) 1974-08-21
SE385941B (sv) 1976-07-26
CH561354A5 (sv) 1975-04-30
JPS5138371B2 (sv) 1976-10-21
BE792224A (fr) 1973-03-30
JPS4863111A (sv) 1973-09-03

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