Ceramic blade with tip seal

Glezer, Boris; Bhardwaj, Narender K; Jones, Russell B

Title: Ceramic blade with tip seal

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Abstract

The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc (66). A shroud assembly (100) is attached to the gas turbine engine (10) and is spaced from the plurality of blades (70) a preestablished distance forming an interface (108) therebetween. Positioned in the interface is a seal (110) having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades (70).

Inventors:

Glezer, Boris ^[1]; Bhardwaj, Narender K ^[2]; Jones, Russell B ^[2]

Del Mar, CA
San Diego, CA

Issue Date:: 1997-01-01

Research Org.:: SOLAR TURBINES INC

OSTI Identifier:: 871079

Patent Number(s):: 5653579

Assignee:: Solar Turbines Incorporated (San Diego, CA)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES

F - MECHANICAL ENGINEERING F16 - ENGINEERING ELEMENTS AND UNITS F16J - PISTONS {

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F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/225 - {by shrouding}
F01D11/08 - for sealing space between rotor blade tips and stator

F - MECHANICAL ENGINEERING F16 - ENGINEERING ELEMENTS AND UNITS F16J - PISTONS {
F16J15/3288 - Filamentary structures, e.g. brush seals

F - MECHANICAL ENGINEERING 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
F05D2220/32 - in gas turbines

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D11/02 - by non-contact sealings, e.g. of labyrinth type

F - MECHANICAL ENGINEERING 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
F05D2240/56 - Brush seals

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DOE Contract Number:: AC21-93MC30246

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: ceramic; blade; tip; seal; gas; turbine; engine; 10; disc; assembly; 64; defining; 66; plurality; blades; 70; attached; thereto; preestablished; rate; thermal; expansion; shroud; 100; spaced; distance; forming; interface; 108; therebetween; positioned; 110; equal; attached thereto; preestablished rate; turbine engine; thermal expansion; gas turbine; ceramic blade; shroud assembly; tip seal; disc assembly; /415/

Citation Formats


                    Glezer, Boris, Bhardwaj, Narender K, and Jones, Russell B. Ceramic blade with tip seal.  United States: N. p., 1997. 
        Web.

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                    Glezer, Boris, Bhardwaj, Narender K, & Jones, Russell B. Ceramic blade with tip seal.  United States.

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                    Glezer, Boris, Bhardwaj, Narender K, and Jones, Russell B. Wed .  
        "Ceramic blade with tip seal".  United States.  https://www.osti.gov/servlets/purl/871079.

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@article{osti_871079,

  title        = {Ceramic blade with tip seal},

  author       = {Glezer, Boris and Bhardwaj, Narender K and Jones, Russell B},

  abstractNote = {The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc (66). A shroud assembly (100) is attached to the gas turbine engine (10) and is spaced from the plurality of blades (70) a preestablished distance forming an interface (108) therebetween. Positioned in the interface is a seal (110) having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades (70).},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {1997},

  month        = {1}

}

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