US3880550A - Outer seal for first stage turbine - Google Patents

Outer seal for first stage turbine Download PDF

Info

Publication number
US3880550A
US3880550A US445047A US44504774A US3880550A US 3880550 A US3880550 A US 3880550A US 445047 A US445047 A US 445047A US 44504774 A US44504774 A US 44504774A US 3880550 A US3880550 A US 3880550A
Authority
US
United States
Prior art keywords
pwa
base material
seal
high strength
bonded
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.)
Expired - Lifetime
Application number
US445047A
Inventor
Arthur F Corey
Bruce E Snyder
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.)
US Air Force
Original Assignee
US Air Force
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 US Air Force filed Critical US Air Force
Priority to US445047A priority Critical patent/US3880550A/en
Application granted granted Critical
Publication of US3880550A publication Critical patent/US3880550A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S277/00—Seal for a joint or juncture
    • Y10S277/922—Bonding or joining for manufacture of seal

Definitions

  • ABSTRACT An outer air seal for the first stage turbine of an engine having the seal segments made of a high strength base material with a highly oxidation-corrosion resistant abradable alloy layer bonded to the surface thereof on the side adjacent the rotor blade. Another embodiment having an abrasive layer bonded to the high strength base material with the abradable layer being bonded to the abrasive layer.
  • the outer air seals for the first stage turbine of the TF30 engine and the JT9D engine use a single material for the seal segments.
  • the material is selected with a compromise between strength and corrosion resistance.
  • abradable surfaces on the seals have prior art structure except the seal 14.
  • the seal segments 16, one of which is shown in FIG. 2 have a base member 24 of a material PWA 647 or PWA 663 with highly oxidation-corrosion resistant abradable layer 26 of PWA 1045 NiCrAlY diffusion bonded to the base material by heating for 1 hour to between 1,300 and 1.400F in a vacuum at a pressure between 145 and 275 meganewtons per square meter and then postheating two hours to between 1,900 and 2,l50F at a pressure of about 15 meganewtons per square meter. Before bonding the surfaces are cleaned by sanding and then either chemical polishing or electropolishing.
  • the material PWA 662, PWA 647 and PWA 1045 will be described in greater detail below.
  • PWA 1045 PWA 663 PWA 647 WS 6 Aluminum 55 6.0 Bismuth 0.5 PPM max Boron 0.003 max 0.015 0.01 max Carbon 0.05 0.1 1 0.6 0.9 Chromium 16.00 8.0 23.4 25.0 Cobalt 10.0 Remainder Remainder Columbium 0.10 max 1.0 Iron 0.75 max 0.35 max 1.50 max 1 0 Lead 10 PPM max Manganese 0.50 max 0.20 max 0.10 max Molybdenum 6.0 Nickel Remainder Remainder 10.0 15.0 Phosphorous 0.015 max Silicon 0.40 max 0.25 max 0.40 max Sulfur 0.015 max 0.015 max 0.015 max Tantalum 4.25 3.5 2.75 Titanium 1.0 0.2 0.9 Tungsten 0.10 max 7.0 7.75 Yttrium 0.2 Zirconium 0.075 0.45 0.4
  • FIG. 1 is a partially schematic cut away sectional Them 15 thus provldefi an P Outer Seal of view of the first stage turbine of an engine with the the first slage Ofa turbme engmeouter air seal of the invention.
  • FIG. 2 is an elongated sectional view of an outer air seal of the device of FIG. 1.
  • FIG. 3 is an enlarged sectional view of an outer air seal for the device of FIG. 1 according to another embodiment of the invention.
  • FIG. 1 of the drawing shows the first stage rotor assembly 10 having rotor blades 12, one of which is shown. positioned adjacent the outer air seal 14.
  • the outer air seal 14 has a plurality of segments 16 positioned around the rotor assembly.
  • the segments 16 are supported on support elements 18 and 20 on a support member 21 which are supported on the outer case 22. All of this structure is comprising an annular seal segment support member surrounding the blades of the first stage of the turbine engine; a plurality of seal segments supported on the seal segment support member; said seal segments having a layer of PWA 1045 sheet material bonded to a high strength Nickel-Chrominum alloy base material.

Abstract

An outer air seal for the first stage turbine of an engine having the seal segments made of a high strength base material with a highly oxidation-corrosion resistant abradable alloy layer bonded to the surface thereof on the side adjacent the rotor blade. Another embodiment having an abrasive layer bonded to the high strength base material with the abradable layer being bonded to the abrasive layer.

Description

United States Patent 1 Corey et al.
.[ Apr. 29, 1975 1 OUTER SEAL FOR FIRST STAGE TURBINE [75] Inventors: Arthur F. Corey. Glastonbury:
Bruce E. Snyder. South Windsor. both of Conn.
[731 Assignee: The United States of America as represented by the Secretary of the Air Force, Washington. DC.
[22] Filed: Feb. 22, 1974 [21] Appl. No.: 445.047
[52] US. Cl 415/174; 277/96 [51] Int. Cl. F0ld 11/00 [58] Field of Search 415/174', 277/96 [56] References Cited UNITED STATES PATENTS 2.742224 4/1956 Burhans 415/174 3.092.306 6/1963 Edcr 415/174 3.291.382 12/1966 Blackhurst et 415/174 3.537.713 11/1970 Matthews et al. 415/174 Primary E.\'uminerRobert 1. Smith ASS/Mil!!! E.\'aminerRobert 1. Smith Allvrney. Agent. or Firm-Harry A. Herbert, Jr.; Richard J. Killoren [57] ABSTRACT An outer air seal for the first stage turbine of an engine having the seal segments made of a high strength base material with a highly oxidation-corrosion resistant abradable alloy layer bonded to the surface thereof on the side adjacent the rotor blade. Another embodiment having an abrasive layer bonded to the high strength base material with the abradable layer being bonded to the abrasive layer.
4 Claims, 3 Drawing Figures OUTER SEAL FOR FIRST STAGE TURBINE RIGHTS OF THE GOVERNMENT The invention described herein may be manufactured and used by or for the Government of the United States for all governmental purposes without the payment of any royalty.
BACKGROUND OF THE INVENTION The outer air seals for the first stage turbine of the TF30 engine and the JT9D engine use a single material for the seal segments. The material is selected with a compromise between strength and corrosion resistance. In the past, abradable surfaces on the seals have prior art structure except the seal 14.
The seal segments 16, one of which is shown in FIG. 2, have a base member 24 of a material PWA 647 or PWA 663 with highly oxidation-corrosion resistant abradable layer 26 of PWA 1045 NiCrAlY diffusion bonded to the base material by heating for 1 hour to between 1,300 and 1.400F in a vacuum at a pressure between 145 and 275 meganewtons per square meter and then postheating two hours to between 1,900 and 2,l50F at a pressure of about 15 meganewtons per square meter. Before bonding the surfaces are cleaned by sanding and then either chemical polishing or electropolishing. The material PWA 662, PWA 647 and PWA 1045 will be described in greater detail below.
been used but these have been unsuccessful since a A modlficatlon of the devlce of FIGS. 1 and 2 compound of sufficient abradabihty without undesirshown in FIG. 3. In this device. the seal segments 16 able side effects, such as corrosion, had not been have a layer 28 of abrasive material WS-6 bonded to found. Thus, abradable surfaces were eliminated and the desi n returned to sin le material se'tl se ments the base member wlth the abradable layer 26 of PWA g g g 1045 being bonded to the abrasive layer 28. This will BRIEF SUMMARY OF THE INVENTION allow incrusion of the moving rotor blade tip into the A I abradable layer until it reaches the abrasive layer Ccor mg to f bed g are T whereupon some machining of the blade tip by the vlded for the outer seal of the first stage turbine abrasive laygr would occur wherein a highly oxidation-corrosion resistant abradas The Composition f the materials PWA 1045 PWA able alloy 15 bonded to a strong high temperature alloy, 661 PWA 647 d W5 5 are given i h f ll i thus eliminating the property compromise necessitated table wherein the parts by weight given are of 100 total by the use of a single alloy. In another embodiment, an parts.
PWA 1045 PWA 663 PWA 647 WS 6 Aluminum 55 6.0 Bismuth 0.5 PPM max Boron 0.003 max 0.015 0.01 max Carbon 0.05 0.1 1 0.6 0.9 Chromium 16.00 8.0 23.4 25.0 Cobalt 10.0 Remainder Remainder Columbium 0.10 max 1.0 Iron 0.75 max 0.35 max 1.50 max 1 0 Lead 10 PPM max Manganese 0.50 max 0.20 max 0.10 max Molybdenum 6.0 Nickel Remainder Remainder 10.0 15.0 Phosphorous 0.015 max Silicon 0.40 max 0.25 max 0.40 max Sulfur 0.015 max 0.015 max 0.015 max Tantalum 4.25 3.5 2.75 Titanium 1.0 0.2 0.9 Tungsten 0.10 max 7.0 7.75 Yttrium 0.2 Zirconium 0.075 0.45 0.4
abrasive material is bonded to the high strength mate- The terms PWA 1045, PWA 663, PWA 647 and rial with the highly oxidation-corrosion resistant layer S-6 as us d in th specification and clalms will Indibeing bonded to the abrasive material. Cate the Composition as given in thls table- In some applications, other alloys than those given IN THE DRAWING may be used for the base member 24. FIG. 1 is a partially schematic cut away sectional Them 15 thus provldefi an P Outer Seal of view of the first stage turbine of an engine with the the first slage Ofa turbme engmeouter air seal of the invention. We
1. An outer seal for the first stage of a turbine engine,
FIG. 2 is an elongated sectional view of an outer air seal of the device of FIG. 1.
FIG. 3 is an enlarged sectional view of an outer air seal for the device of FIG. 1 according to another embodiment of the invention.
DETAILED DESCRIPTION OF THE INVENTION Reference is now made to FIG. 1 of the drawing which shows the first stage rotor assembly 10 having rotor blades 12, one of which is shown. positioned adjacent the outer air seal 14. The outer air seal 14 has a plurality of segments 16 positioned around the rotor assembly. The segments 16 are supported on support elements 18 and 20 on a support member 21 which are supported on the outer case 22. All of this structure is comprising an annular seal segment support member surrounding the blades of the first stage of the turbine engine; a plurality of seal segments supported on the seal segment support member; said seal segments having a layer of PWA 1045 sheet material bonded to a high strength Nickel-Chrominum alloy base material.
2. The device as recited in claim 1 wherein the high strength base material is PWA 663.
3. The device as recited in claim 1 wherein the high strength base material is PWA 647.
4. The device as recited in claim 1 wherein an abrasive layer of WS-6 is bonded to the high strength base material between the base material and the sheet of PWA 1045.

Claims (4)

1. An outer seal for the first stage of a turbine engine, comprising an annular seal segment support member surrounding the blades of the first stage of the turbine engine; a plurality of seal segments supported on the seal segment support member; said seal segments having a layer of PWA 1045 sheet material bonded to a high strength Nickel-Chrominum alloy base material.
2. The device as recited in claim 1 wherein the high strength base material is PWA 663.
3. The device as recited in claim 1 wherein the high strength base material is PWA 647.
4. The device as recited in claim 1 wherein an abrasive layer of WS-6 is bonded to the high strength base material between the base material and the sheet of PWA 1045.
US445047A 1974-02-22 1974-02-22 Outer seal for first stage turbine Expired - Lifetime US3880550A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US445047A US3880550A (en) 1974-02-22 1974-02-22 Outer seal for first stage turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US445047A US3880550A (en) 1974-02-22 1974-02-22 Outer seal for first stage turbine

Publications (1)

Publication Number Publication Date
US3880550A true US3880550A (en) 1975-04-29

Family

ID=23767406

Family Applications (1)

Application Number Title Priority Date Filing Date
US445047A Expired - Lifetime US3880550A (en) 1974-02-22 1974-02-22 Outer seal for first stage turbine

Country Status (1)

Country Link
US (1) US3880550A (en)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3975165A (en) * 1973-12-26 1976-08-17 Union Carbide Corporation Graded metal-to-ceramic structure for high temperature abradable seal applications and a method of producing said
DE2937463A1 (en) * 1978-09-22 1980-04-03 Gen Electric GASKET FOR TURBINE ENGINE COVER
US4207024A (en) * 1977-05-27 1980-06-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4336276A (en) * 1980-03-30 1982-06-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fully plasma-sprayed compliant backed ceramic turbine seal
US4349313A (en) * 1979-12-26 1982-09-14 United Technologies Corporation Abradable rub strip
GB2116639A (en) * 1982-03-05 1983-09-28 Rolls Royce Turbine shroud segments and turbine shroud assembly
DE3326535A1 (en) * 1982-08-09 1984-03-01 United Technologies Corp., 06101 Hartford, Conn. DEVICE WITH A GASWEG SEALING SYSTEM BETWEEN RELATIVELY MOVING PARTS
US4669955A (en) * 1980-08-08 1987-06-02 Rolls-Royce Plc Axial flow turbines
US4925365A (en) * 1988-08-18 1990-05-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine stator ring assembly
US5456578A (en) * 1992-07-29 1995-10-10 Aisin Seiki Kabushiki Kaisha Turbine housing of turbocharger
US5837385A (en) * 1997-03-31 1998-11-17 General Electric Company Environmental coating for nickel aluminide components and a method therefor
US6365222B1 (en) 2000-10-27 2002-04-02 Siemens Westinghouse Power Corporation Abradable coating applied with cold spray technique
US20090175727A1 (en) * 2008-01-08 2009-07-09 United Technologies Corporation Dimensional restoration of stationary shroud segments
US20100164179A1 (en) * 2008-01-25 2010-07-01 Yuichi Hirakawa Seal structure
US20110002771A1 (en) * 2009-07-03 2011-01-06 Rolls-Royce Plc Rotor blade over-tip leakage control
US20110101619A1 (en) * 2008-03-04 2011-05-05 David Fairbourn A MCrAlY Alloy, Methods to Produce a MCrAlY Layer and a Honeycomb Seal
WO2011156808A1 (en) * 2010-06-11 2011-12-15 Grondahl Clayton M Film riding pressure actuated leaf seal assembly
US20190085865A1 (en) * 2017-09-19 2019-03-21 United Technologies Corporation Turbine engine seal for high erosion environment

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2742224A (en) * 1951-03-30 1956-04-17 United Aircraft Corp Compressor casing lining
US3092306A (en) * 1958-04-28 1963-06-04 Gen Motors Corp Abradable protective coating for compressor casings
US3291382A (en) * 1964-05-08 1966-12-13 Rolls Royce Bladed structure, for example, for a gas turbine engine compressor
US3537713A (en) * 1968-02-21 1970-11-03 Garrett Corp Wear-resistant labyrinth seal

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2742224A (en) * 1951-03-30 1956-04-17 United Aircraft Corp Compressor casing lining
US3092306A (en) * 1958-04-28 1963-06-04 Gen Motors Corp Abradable protective coating for compressor casings
US3291382A (en) * 1964-05-08 1966-12-13 Rolls Royce Bladed structure, for example, for a gas turbine engine compressor
US3537713A (en) * 1968-02-21 1970-11-03 Garrett Corp Wear-resistant labyrinth seal

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3975165A (en) * 1973-12-26 1976-08-17 Union Carbide Corporation Graded metal-to-ceramic structure for high temperature abradable seal applications and a method of producing said
US4207024A (en) * 1977-05-27 1980-06-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
DE2937463A1 (en) * 1978-09-22 1980-04-03 Gen Electric GASKET FOR TURBINE ENGINE COVER
US4349313A (en) * 1979-12-26 1982-09-14 United Technologies Corporation Abradable rub strip
US4336276A (en) * 1980-03-30 1982-06-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fully plasma-sprayed compliant backed ceramic turbine seal
US4669955A (en) * 1980-08-08 1987-06-02 Rolls-Royce Plc Axial flow turbines
GB2116639A (en) * 1982-03-05 1983-09-28 Rolls Royce Turbine shroud segments and turbine shroud assembly
DE3326535A1 (en) * 1982-08-09 1984-03-01 United Technologies Corp., 06101 Hartford, Conn. DEVICE WITH A GASWEG SEALING SYSTEM BETWEEN RELATIVELY MOVING PARTS
US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
US4925365A (en) * 1988-08-18 1990-05-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine stator ring assembly
US5456578A (en) * 1992-07-29 1995-10-10 Aisin Seiki Kabushiki Kaisha Turbine housing of turbocharger
US5837385A (en) * 1997-03-31 1998-11-17 General Electric Company Environmental coating for nickel aluminide components and a method therefor
US6365222B1 (en) 2000-10-27 2002-04-02 Siemens Westinghouse Power Corporation Abradable coating applied with cold spray technique
US20090175727A1 (en) * 2008-01-08 2009-07-09 United Technologies Corporation Dimensional restoration of stationary shroud segments
US20100164179A1 (en) * 2008-01-25 2010-07-01 Yuichi Hirakawa Seal structure
US8240675B2 (en) * 2008-01-25 2012-08-14 Mitsubishi Heavy Industries, Ltd. Seal structure
US20110101619A1 (en) * 2008-03-04 2011-05-05 David Fairbourn A MCrAlY Alloy, Methods to Produce a MCrAlY Layer and a Honeycomb Seal
US8708646B2 (en) * 2008-03-04 2014-04-29 Siemens Aktiengesellschaft MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal
US20110002771A1 (en) * 2009-07-03 2011-01-06 Rolls-Royce Plc Rotor blade over-tip leakage control
US8545175B2 (en) 2009-07-03 2013-10-01 Rolls-Royce Plc Rotor blade over-tip leakage control
WO2011156808A1 (en) * 2010-06-11 2011-12-15 Grondahl Clayton M Film riding pressure actuated leaf seal assembly
US8474827B2 (en) 2010-06-11 2013-07-02 Cmg Tech, Llc Film riding pressure actuated leaf seal assembly
US20190085865A1 (en) * 2017-09-19 2019-03-21 United Technologies Corporation Turbine engine seal for high erosion environment
US11149744B2 (en) * 2017-09-19 2021-10-19 Raytheon Technologies Corporation Turbine engine seal for high erosion environment

Similar Documents

Publication Publication Date Title
US3880550A (en) Outer seal for first stage turbine
US2914300A (en) Nozzle vane support for turbines
US4460185A (en) Seal including a non-metallic abradable material
US6533285B2 (en) Abradable coating and method of production
US4336276A (en) Fully plasma-sprayed compliant backed ceramic turbine seal
EP1801472B1 (en) Sealing device
US10018056B2 (en) Abrasive coating and manufacture and use methods
US11752578B2 (en) Abrasive preforms and manufacture and use methods
US6610416B2 (en) Material treatment for reduced cutting energy and improved temperature capability of honeycomb seals
GB1377788A (en) Arrangement for retaining a ceramic turbine blade in a slotted steel rotor or blade seating ring
RU2615088C2 (en) Seal, seal of turbine engine and method of producing the seal
US11028721B2 (en) Coating to improve oxidation and corrosion resistance of abrasive tip system
US10012095B2 (en) Abrasive coating and manufacture and use methods
EP3597860A1 (en) Coating to improve oxidation and corrosion resistance of abrasive tip system
US10030527B2 (en) Abrasive preforms and manufacture and use methods
US2840343A (en) Reduction of rotating tip clearance using segmented wear strips
US8708659B2 (en) Turbine engine component having protective coating
FI60037C (en) SKYDDSBELAEGGNING PAO STAOLYTA
US3754839A (en) Filament reinforced rotor assembly
US3765796A (en) Filament reinforced rotor assembly
US3787141A (en) Filament reinforced motor assembly
US20030062256A1 (en) Method of making labyrinth seal lips for the moving parts of turbomachines
US4438956A (en) Joining of components
Evans et al. Preliminary investigation of a single-shaft Brayton rotating unit designed for a 2 to 10-kilowatt space power generation system
WALLACE Development of abrasive blade tip coatings for use in an abradable turbine gas path seal system[Final Report, 1 Jan.- 31 Dec. 1976]