GB1149549A - Creation of Inventions and Patents with Artificial Intelligence

GB1149549A – Composite compressor or like rotor blades
– Google Patents

GB1149549A – Composite compressor or like rotor blades
– Google Patents
Composite compressor or like rotor blades

Info

Publication number
GB1149549A

GB1149549A
GB12965/68A
GB1296568A
GB1149549A
GB 1149549 A
GB1149549 A
GB 1149549A
GB 12965/68 A
GB12965/68 A
GB 12965/68A
GB 1296568 A
GB1296568 A
GB 1296568A
GB 1149549 A
GB1149549 A
GB 1149549A
Authority
GB
United Kingdom
Prior art keywords
resin
filaments
mould
mandrel
sheet
Prior art date
1967-07-12
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

Application number
GB12965/68A
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.)

Motors Liquidation Co

Original Assignee
Motors Liquidation Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
1967-07-12
Filing date
1968-03-18
Publication date
1969-04-23

1968-03-18
Application filed by Motors Liquidation Co
filed
Critical
Motors Liquidation Co

1969-04-23
Publication of GB1149549A
publication
Critical
patent/GB1149549A/en

Status
Expired
legal-status
Critical
Current

Links

Espacenet

Global Dossier

Discuss

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

F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments

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

F01D5/14—Form or construction

F01D5/16—Form or construction for counteracting blade vibration

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

Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

Y10T29/00—Metal working

Y10T29/49—Method of mechanical manufacture

Y10T29/49316—Impeller making

Y10T29/49336—Blade making

Y10T29/49337—Composite blade

Abstract

1,149,549. Moulding rotor blades. GENERAL MOTORS CORP. 18 March, 1968 [12 July, 1967], No. 12965/68. Heading B5A. [Also in Division F1] A composite compressor or like rotor blade comprises a metal aerofoil member (12) having a stiffening coating layer (26) of filaments bonded together in parallel side by side relationship by a thermosetting resin. The filaments have a modulus of elasticity of at least 40 x 106 1b./in.2 and may be formed of pure boron deposited on a tungsten wire core, or of graphite or silicon carbide, the bonding agent being epoxy, polyimide or polybenzimadazole resin. The metal member (12) may be titanium or aluminium or alloys thereof, steel, or copper alloys such as brass or bronze. Sheets of the filaments are formed by coating an aluminium cylindrical mandrel with a sheet of polyvinyl chloride film, heating the mandrel to about 95 F., coating the film with resin and then rotating the mandrel so as to wind a continuous filament thereon. The filament passes through a cleaning tank of toluene during the winding operation. The wound filament is then coated with resin and wrapped with a further sheet of polyvinyl chloride film, after which the sheet and filament sandwich is removed from the mandrel by cutting through the sandwich along the length of the mandrel. The sandwich is clamped to a piece of wood and partially cured in an oven for 50 minutes at 165 F., the result being a sheet of parallel, bonded filaments. Sections corresponding to the convex and concave faces of the aerofoil metal member (12) are then cut from the sheet, placed over the cleaned and etched faces of the member and inserted in an aluminium reinforced resin mould. The mould is subjected to a pressure of 200 1b./in.2 and heated for 1 hour at 200 F. The composite blade is then removed from the mould, coated with resin, replaced in the mould, and cured for 1 hour at 200 F. and a further hour at 300 F. under 200 1b./in.2 pressure. The blade is removed from the mould and the cure completed at 300 F. in a forced draught oven for 2 hours. The resin used may consist of 100 parts by weight of epoxy resin, 1O1 parts of methyl nadic anhydride and 1À5 parts oftri-dimethylaminomethylphenol catalyst. Several layers of filaments may be bonded to the metal member, the filaments being parallel in each layer but differing in direction to those of other layers.

GB12965/68A
1967-07-12
1968-03-18
Composite compressor or like rotor blades

Expired

GB1149549A
(en)

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

US652749A

US3368795A
(en)

1967-07-12
1967-07-12
Composite rotor blade having high modal frequencies

Publications (1)

Publication Number
Publication Date

GB1149549A
true

GB1149549A
(en)

1969-04-23

Family
ID=24618002
Family Applications (1)

Application Number
Title
Priority Date
Filing Date

GB12965/68A
Expired

GB1149549A
(en)

1967-07-12
1968-03-18
Composite compressor or like rotor blades

Country Status (2)

Country
Link

US
(1)

US3368795A
(en)

GB
(1)

GB1149549A
(en)

Cited By (1)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US4248649A
(en)

1978-01-19
1981-02-03
Rolls-Royce Limited
Method for producing a composite structure

Families Citing this family (26)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US3679324A
(en)

1970-12-04
1972-07-25
United Aircraft Corp
Filament reinforced gas turbine blade

US3717419A
(en)

1971-07-09
1973-02-20
Susquehanna Corp
Turbine blade

US3796513A
(en)

1972-06-19
1974-03-12
Westinghouse Electric Corp
High damping blades

FR2195255A5
(en)

1972-08-04
1974-03-01
Snecma

US4118147A
(en)

1976-12-22
1978-10-03
General Electric Company
Composite reinforcement of metallic airfoils

US4178667A
(en)

1978-03-06
1979-12-18
General Motors Corporation
Method of controlling turbomachine blade flutter

US4292010A
(en)

1978-09-16
1981-09-29
Rolls-Royce Limited
Cambered blade or vane for a gas turbine engine

US4472866A
(en)

1982-03-01
1984-09-25
Trw Inc.
Method of making an airfoil

US4583274A
(en)

1982-03-01
1986-04-22
Trw Inc.
Method of making an airfoil

US4465434A
(en)

1982-04-29
1984-08-14
Williams International Corporation
Composite turbine wheel

US5118257A
(en)

1990-05-25
1992-06-02
Sundstrand Corporation
Boot attachment for composite turbine blade, turbine blade and method of making turbine blade

US5314309A
(en)

1990-05-25
1994-05-24
Anthony Blakeley
Turbine blade with metallic attachment and method of making the same

US5275535A
(en)

1991-05-31
1994-01-04
Innerspace Corporation
Ortho skew propeller blade

CA2070522A1
(en)

1991-07-22
1993-01-23
Jan C. Schilling
Layup of composite fan blades/vanes

FR2682992B1
(en)

1991-10-23
1995-04-21
Snecma

BLADE OF A TURBOMACHINE IN A MATRIX COMPOSITE MATRIX BASED ON AN ELASTOMER.

US5490764A
(en)

1994-05-23
1996-02-13
General Electric Company
Unshrouded blading for high bypass turbofan engines

CA2450764C
(en)

2001-06-26
2013-12-10
Vita-Mix Corporation
Container for a blender

US20070036658A1
(en)

2005-08-09
2007-02-15
Morris Robert J
Tunable gas turbine engine fan assembly

US7360997B2
(en)

2005-10-06
2008-04-22
General Electric Company
Vibration damper coating

US20110182741A1
(en)

2010-01-26
2011-07-28
United Technologies Corporation
Composite fan blade leading edge recamber

EP2896789B1
(en)

2014-01-16
2018-03-07
United Technologies Corporation
Fan blade with variable thickness composite cover

DE102015203868A1
(en)

2015-03-04
2016-09-08
Rolls-Royce Deutschland Ltd & Co Kg

Fan blade for a propulsion system

BE1023299B1
(en)

2016-01-21
2017-01-26
Safran Aero Boosters S.A.

Stator blade

US10641281B2
(en)

2016-08-08
2020-05-05
United Technologies Corporation
Mistuned laminate airfoil

US11149558B2
(en)

2018-10-16
2021-10-19
General Electric Company
Frangible gas turbine engine airfoil with layup change

US10837286B2
(en)

2018-10-16
2020-11-17
General Electric Company
Frangible gas turbine engine airfoil with chord reduction

Family Cites Families (4)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US2775426A
(en)

1951-12-20
1956-12-25
Westinghouse Electric Corp
Blade structure

GB787500A
(en)

1955-05-12
1957-12-11
Rolls Royce
Improvements relating to axial flow compressor blading and methods of manufacture thereof

US2920868A
(en)

1955-10-05
1960-01-12
Westinghouse Electric Corp
Dampened blade structure

US3301530A
(en)

1965-08-03
1967-01-31
Gen Motors Corp
Damped blade

1967

1967-07-12
US
US652749A
patent/US3368795A/en
not_active
Expired – Lifetime

1968

1968-03-18
GB
GB12965/68A
patent/GB1149549A/en
not_active
Expired

Cited By (1)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

US4248649A
(en)

1978-01-19
1981-02-03
Rolls-Royce Limited
Method for producing a composite structure

Also Published As

Publication number
Publication date

US3368795A
(en)

1968-02-13

Contact information