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1. (WO1984000049) COAXIAL TURBOMACHINE
Note: Text based on automatic Optical Character Recognition processes. Please use the PDF version for legal matters

CLAIMS

1. A rotary vaned machine (10/110/76)
comprising:
a plurality of coaxially aligned blade
carrying means (12,112,212/14,114,214/16,116,216)
including a first (14/114/214) , second (12/112/212) and third (16/116/216) blade carrying means;
blades (30-45/130-133/230-233) on each of
said blade carrying means? and
means . (69/169/269) mounting said first,
second and third blade carrying means for relative
rotation, each to the other.

2. The rotary vaned machine (10/110/76) of claim 1 wherein said first (14/114/214) and second
(12/112/212) blade carrying means are rotatable about an axis (15), the extension of the blades (30,32,34,36, 38/40,42,44/130,132/230,232) on said first (14/114/214) and second (12/112/212) blade carrying means from said axis (15) varying progressively between an inlet (20) and outlet (22) end and means (68/72,74/272,274) for
effecting relative rotation of said first and second
blade carrying means such that said first blade carrying means can be rotated at a greater rotational
velocity than said second blade carrying means.

wiFO

3. The rotary vaned machine (10/110/76) of claims 2 wherein said means (68/72,74/272,274) for
effecting relative rotation of said first (14/114/214) and second (12/112/212) blade carrying means is con- structed and arranged such that the tip speeds of the blades on said first and second blade carrying means is approximately the same.

4. A rotary vaned machine (10/110/76)
comprising:
. a plurality of coaxially aligned blade
carrying means (12,112,212/14,114,214/16,116,216)
including a first (14/114/214) and second (12/112/212) blade carrying means, which, in conjunction with a
stationary third blade carrying means (16/116/216)
define an annular passageway of progressively increasing, radius between an inlet (20) and outlet (22) of the rotary vaned machine;
a plurality of blades (30-45/130-133/230-233) in said passageway and respectively extending from said first, second and third blade carrying means; and
means (69/169/269) mounting said first and second blade carrying means for relative rotation with respect to each other.

5. The rotary vaned machine (10/110/76) of claim 4 including means (68/72,74/272,274) for effecting predetermined relative rotation between said
first (14/114/214) and second (12/112/212) blade
carrying means.

OMPI

6. A multistage centrifugal compressor
(10/110) comprising:
a plurality of coaxially aligned rotors
(12,112/14,114);
a plurality of compressor blades (30,32,34,36,

38/40,42,44/130,132) mounted on each of said coaxially aligned rotors;
a stator (16/116) coaxially aligned with said rotors;
a plurality of diffuser blades (31,33,35,37,

39,41,43,45/131,133) on said stator and arranged between -said compressor blades;
said rotors, compressor blades and diffuser blades defining a plurality of stages (30,31-44,45)/
(130,313-132,133);
said rotors and said stator defining an
annular gas flow passageway (18) communicating between an inlet (20) and outlet (22) , said gas flow passageway increasing in radius towards said outlet (22) ; and
means (68/72,74/272,274) for rotating said compressor blades (30,32,34,36,38/130) in one of the stages (30,31-38,39/130,131) nearer said inlet at a greater angular velocity than the blades (40,42,44/132) in one of the stages (40,41-44, 45/132,133) nearer said outlet.

7. The multistage centrifugal compressor
(10/110) of claim 6 wherein the diffuser blades
(31,33,35,37,39,41,43,45/131,133) in at least one of said stages are adjustable.

__O PI
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8. The multistage centrifugal compressor (10/110) of claim 6 in combination with a gas turbine engine wherein said compressor constitutes the air intake element of said gas turbine engine.

9. The multistage centrifugal compressor

(10/110) of claim 6 in combination with an engine turbocharger (70) turbine (76) wherein said compressor constitutes the air intake element of said turbocharger.

10. A pentrifugal turbine (76) of more than one stage (230,231/232,233) comprising:
a plurality of coaxially aligned rotors
(212/214) and a stator (216) said rotors and said stator defining an annular gas flow passageway there- between;
a plurality of turbine blades (230/232) carried on said coaxially aligned rotors;
said stator (216) carrying a plurality of nozzle blades (231/233) between said compressor blades;
said rotors, nozzle blades and turbine blades defining a plurality of stages;
said gas flow passageway housing said blades and communicating between an inlet and an outlet wherein the radius of said gas flow passageway de-creases towards said outlet; and
means (272,274) for rotating said turbine blades (230) in one of the stages (230,231) nearer said outlet at a greater angular velocity than the turbine blades (232) in one of the stages (232,233) nearer said inlet.

11. The centripetal turbine (76) of claim 10 wherein the nozzle blades (231,233) in at least one
stage are adjustable.

OMPI WIPO