EP3165774A1 - Compressor with similar coating on compressor blades and compressor casing and gas turbine - Google Patents

Compressor with similar coating on compressor blades and compressor casing and gas turbine Download PDF

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Publication number
EP3165774A1
EP3165774A1 EP15192953.6A EP15192953A EP3165774A1 EP 3165774 A1 EP3165774 A1 EP 3165774A1 EP 15192953 A EP15192953 A EP 15192953A EP 3165774 A1 EP3165774 A1 EP 3165774A1
Authority
EP
European Patent Office
Prior art keywords
compressor
coating
casing
blades
gas turbine
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Withdrawn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
EP15192953.6A
Other languages
German (de)
French (fr)
Inventor
Arturo Flores Renteria
Eckart Schumann
Dimitrios Zois
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP15192953.6A priority Critical patent/EP3165774A1/en
Publication of EP3165774A1 publication Critical patent/EP3165774A1/en
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/289—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps having provision against erosion or for dust-separation
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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 invention relates to a compressor wherein the blades of the compressor have a coating against corrosion and erosion and wherein a similar or same coating is applied on the casing of the compressor and a gas turbine.
  • Ni-Graphite abradable coating is been used to reduce the gap between the compressor blades and casing to increase the efficiency of gas turbines.
  • this coating starts rubbing, the detached coating debries start depositing on the turbine airfoils. It has been demonstrated that these deposits can induce damage of the ceramic thermal barrier coating due to alterations of its thermo-mechanical properties.
  • the figure shows one example of the invention of the compressor blade and an outer casing which are both coated.
  • the compressor 1 has an outer casing 4 and compressor blades 10, which can rotate inside the casing 4.
  • the compressor blades 10 have a coating 13 against corrosion and erosion.
  • the matrix of this coating 13 can be any coating, especially a chromate phosphates based matrix is used.
  • the coating 13 can preferably also be a bilayer made of the same material, but especially with aluminium particles in the underlying layer.
  • a tip 16 of the compressor blade 10 which faces the casing 4 is preferably also coated with the same material of the coating 13.
  • the casing 4, which faces the compressor blade 10 also has a coating 7 along the inner circumference of the casing (4), especially only applied locally opposite to the compressor blade 10, which has the similar composition especially the chromium phosphate matrix.
  • Chromate phosphate based coatings are state of the art and are shown in US 7,789,953 B2 .

Abstract

By applying the same material on the casing opposite to the compressor blade (10) of a compressor (1) a low rear behavior is reached.

Description

  • The invention relates to a compressor wherein the blades of the compressor have a coating against corrosion and erosion and wherein a similar or same coating is applied on the casing of the compressor and a gas turbine.
  • Often a Ni-Graphite abradable coating is been used to reduce the gap between the compressor blades and casing to increase the efficiency of gas turbines. However, once this coating starts rubbing, the detached coating debries start depositing on the turbine airfoils. It has been demonstrated that these deposits can induce damage of the ceramic thermal barrier coating due to alterations of its thermo-mechanical properties.
  • It is therefore the aim of the invention to solve the problems given above.
  • The problem is solved by a compressor according to claim 1 and a gas turbine according to claim 7.
  • In the subclaims further advantages of the invention are shown which can arbitrarily combined with each other to yield further advantages.
  • The figure shows one example of the invention of the compressor blade and an outer casing which are both coated.
  • The figure and the description are only examples of the invention.
  • In the figure a part of the compressor 1 is shown.
    The compressor 1 has an outer casing 4 and compressor blades 10, which can rotate inside the casing 4.
  • The compressor blades 10 have a coating 13 against corrosion and erosion. The matrix of this coating 13 can be any coating, especially a chromate phosphates based matrix is used.
  • The coating 13 can preferably also be a bilayer made of the same material, but especially with aluminium particles in the underlying layer.
  • A tip 16 of the compressor blade 10 which faces the casing 4 is preferably also coated with the same material of the coating 13.
  • The casing 4, which faces the compressor blade 10 also has a coating 7 along the inner circumference of the casing (4), especially only applied locally opposite to the compressor blade 10, which has the similar composition especially the chromium phosphate matrix.
  • Chromate phosphate based coatings are state of the art and are shown in US 7,789,953 B2 .
  • The use of the same or similar coatings (phosphate-matrix) - metal (aluminium-particles) will reduce the alteration of the thermo-mechanical properties. The resulting debries will not induce any of the known damage. Moreover, these type of coatings have a temperature stability up to 873K. The manufacturing costs are very low and the wear behavior is appropriated for this purpose. These coatings are been used as corrosion protective coatings for compressor airfoils.
  • The use of an appropriate coating capable to fulfill the required rubbing behavior and temperature stability while avoiding the impact on the turbine components is advantageous for service conditions.

Claims (7)

  1. Compressor (1),
    with a casing (4)
    in which (4) compressor blades (10) are rotatable,
    wherein the compressor blades (10) have a coating (13), which is optionally also applied on the tip (16) on the compressor blade (10) and
    wherein at least opposite to the tips (16) of the compressor blades (10) the same matrix material of the coating (13) of the compressor blade (10) is applied on the inner surface of the casing (4).
  2. Compressor according to claim 1,
    wherein the coating (7) of the casing (4) is only locally applied opposite to the tips (16) of the compressor blades (10).
  3. Compressor according to one or both of the claims 1, 2,
    wherein the material of the coatings (7, 13) comprises a chromate phosphate matrix.
  4. Compressor according to one or any of the claims 1, 2, or 3,
    wherein the coating (13) of the compressor blades (10) contains aluminium particles.
  5. Compressor according to one or any of the claims 1, 2, 3 or 4,
    wherein the coating (7) of the casing (4) does not contain aluminium particles.
  6. Compressor according to one or any of the claims 1, 2, 3, 4 or 5,
    wherein the coating (13) of the compressor blades (10) is a bilayer, especially with aluminium particles in the underlying layer.
  7. Gas turbine with a compressor according to one of the claims 1 to 6.
EP15192953.6A 2015-11-04 2015-11-04 Compressor with similar coating on compressor blades and compressor casing and gas turbine Withdrawn EP3165774A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15192953.6A EP3165774A1 (en) 2015-11-04 2015-11-04 Compressor with similar coating on compressor blades and compressor casing and gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15192953.6A EP3165774A1 (en) 2015-11-04 2015-11-04 Compressor with similar coating on compressor blades and compressor casing and gas turbine

Publications (1)

Publication Number Publication Date
EP3165774A1 true EP3165774A1 (en) 2017-05-10

Family

ID=54366131

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15192953.6A Withdrawn EP3165774A1 (en) 2015-11-04 2015-11-04 Compressor with similar coating on compressor blades and compressor casing and gas turbine

Country Status (1)

Country Link
EP (1) EP3165774A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10487847B2 (en) 2016-01-19 2019-11-26 Pratt & Whitney Canada Corp. Gas turbine engine blade casing

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060147630A1 (en) * 2004-12-01 2006-07-06 Siemens Aktiengesellschaft Process for coating components in the interior of an apparatus
WO2006126993A1 (en) * 2005-05-24 2006-11-30 Honeywell International Inc. Turbocharger compressor having improved erosion-corrosion resistance
WO2008116757A2 (en) * 2007-03-27 2008-10-02 Alstom Technology Ltd Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same
US7789953B2 (en) 2008-03-28 2010-09-07 Praxair S.T. Technology, Inc. High temperature resistant coating compositions
US20120082541A1 (en) * 2010-09-30 2012-04-05 Enzo Macchia Gas turbine engine casing

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060147630A1 (en) * 2004-12-01 2006-07-06 Siemens Aktiengesellschaft Process for coating components in the interior of an apparatus
WO2006126993A1 (en) * 2005-05-24 2006-11-30 Honeywell International Inc. Turbocharger compressor having improved erosion-corrosion resistance
WO2008116757A2 (en) * 2007-03-27 2008-10-02 Alstom Technology Ltd Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same
US7789953B2 (en) 2008-03-28 2010-09-07 Praxair S.T. Technology, Inc. High temperature resistant coating compositions
US20120082541A1 (en) * 2010-09-30 2012-04-05 Enzo Macchia Gas turbine engine casing

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10487847B2 (en) 2016-01-19 2019-11-26 Pratt & Whitney Canada Corp. Gas turbine engine blade casing

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