Thrust force-compensating apparatus with improved hydraulic pressure-responsive balance mechanism

• US 5,102,295 A
• Filed: 04/03/1990
• Issued: 04/07/1992
• Est. Priority Date: 04/03/1990
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Pope, Adam N.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US07/505,119
• Time in Patent Office: 735 Days
• Field of Search: 415/104, 415/105, 415/107, 415/14
• US Class Current: 415/104
• CPC Class Codes: F01D 25/168 for axial load mainly
• CPC Class Codes: F16C 32/0692 for axial load only
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An axial thrust force-compensating apparatus is provided in a gas turbine engine having relatively rotatable first and second structures. The axial thrust force-compensating apparatus includes a first annular part mounted to the first engine structure and having an annular end surface, a second annular part mounted to the second engine structure and having an annular end surface which opposes and faces toward the end surface of the first annular part, and a primary hydraulic pressure balance mechanism for providing separate outer and inner fluid flows to the respective outer and inner regions between the end surfaces at pressures responsive to the amount of separation existing between the end surfaces at those regions. The separate fluid flows at the pressures produce a film of fluid flowing between and in contact with the respective end surfaces which generates primary compensating moment forces acting on the end surfaces to maintain the end surfaces in generally parallel relationship. The improved apparatus also has a secondary hydraulic pressure balance mechanism for producing secondary compensating moment forces which complement the primary compensating moment forces produced by the primary pressure balance mechanisms to limit the magnitude of any non-parallel relationship between the end surfaces of the first and second parts.

Claims

1. In a gas turbine engine having relatively rotatable first and second structures, an axial thrust force-compensating apparatus comprising:

(a) a first annular part mounted to said first engine structure and having an annular end surface;

(b) a second annular part mounted to said second engine structure and having an annular end surface which opposes and faces toward said annular end surface of said first annular part; and

(c) primary hydraulic pressure balance means defined in said first annular part for providing separate outer and inner fluid flows through said first part to respective outer and inner regions between said end surfaces of said first and second parts at respective first and second pressures responsive to the amount of separation existing between said end surfaces at said regions, said separate fluid flows at said first and second pressures producing a film of fluid flowing between and in contact with said respective end surfaces which generates primary compensating moment forces acting on said end surfaces to maintain said end surfaces in generally parallel relationship.

2. The apparatus as recited in claim 1, wherein said primary pressure balance means includes a plurality of hydrostatic pockets defined in said annular end surface of said first annular part, each pocket spanning a separate arcuate portion of said annular end surface and facing toward said end surface of said second annular part, each pocket being formed by a pair of radially spaced and separate outer and inner arcuate-shaped grooves being unconnected to one another.

3. The apparatus as recited in claim 2, wherein said primary pressure balance means also includes outer and inner pluralities of flow control orifices defined in said first annular part for receiving a pressurized flow of fluid, said outer orifices opening in said outer grooves and said inner orifices opening in said inner grooves for communicating said inner and outer fluid flows to said respective outer and inner grooves at said first and second pressures responsive to the amount of separation existing between said end surfaces of said first and second annular parts.

4. The apparatus as recited in claim 1, further comprising:

secondary hydraulic pressure balance means defined in said second annular part for producing secondary compensating moment forces which complement said primary compensating moment forces produced by said primary pressure balance means to limit the magnitude of any non-parallel relationship between said end surfaces of said first and second parts.

5. The apparatus as recited in claim 4, wherein said secondary pressure balance means includes circumferentially-spaced non-intersecting pluralities of first and second conduits formed in said second part and extending generally in opposite diametric relationships across said second part from said end surface thereof toward an opposite end surface thereof.

6. The apparatus as recited in claim 5, wherein said secondary pressure balance means also includes:

outer and inner annular compartments defined at said opposite end surface of said second part;

said first and second conduits extending and providing flow communication between respective outer and inner grooves in said end surface of said first part and said inner and outer compartments at said opposite end surface of said second part.

7. The apparatus as recited in claim 5, wherein said secondary pressure balance means also includes radially-spaced non-intersecting pluralities of third and fourth conduits intersecting with said respective first and second conduits and extending and providing flow communication between said first and second conduits and opposite outer and inner annular surfaces of said second part.

8. The apparatus as recited in claim 7, wherein said first and second conduits extend to and open at said opposite end surface of said second part.

9. The apparatus as recited in claim 7, wherein said first and second conduits terminate midway across said second part where they intersect with said respective third and fourth conduits.

10. In a gas turbine engine having relatively rotatable first and second structures with respective annular cavities which face toward one another, an axial thrust force-compensating apparatus, comprising:

(a) a first annular part mounted in said annular cavity of said first engine structure and having an annular end surface;

(b) a second annular part mounted in said annular cavity of said second engine structure and having an annular end surface which opposes and faces toward said end surface of said first annular part;

(c) primary hydraulic pressure balance means defined in said first annular part for providing separate outer and inner fluid flows through said first part to respective outer and inner regions between said end surfaces of said first and second parts at pressures responsive to the amount of separation existing between said end surfaces at said regions, said separate fluid flows at said pressures producing a film of fluid flowing between and in contact with said respective end surfaces which generates primary compensating moment forces acting on said end surfaces to maintain said end surfaces in generally parallel relationship; and

(d) secondary hydraulic pressure balance means defined in said second annular part for producing secondary compensating moment forces which complement said primary compensating moment forces produced by said primary pressure balance means to limit the magnitude of any non-parallel relationship between said end surfaces of said first and second parts.

11. The apparatus as recited in claim 10, wherein said primary pressure balance means includes a plurality of hydrostatic pockets defined in said annular end surface of said first annular part, each pocket spanning a separate arcuate portion of said annular end surface and facing toward said end surface of said second annular part, each pocket being formed by a pair of radially spaced and separate outer and inner arcuate-shaped grooves being unconnected to one another.

12. The apparatus as recited in claim 11, wherein said primary pressure balance means also includes outer and inner pluralities of flow control orifices defined in said first annular part for receiving a pressurized flow of fluid, said outer orifices opening in said outer grooves and said inner orifices opening in said inner grooves for communicating said inner and outer fluid flows to said respective outer and inner grooves at said pressures responsive to the amount of separation existing between said end surfaces of said first and second annular parts.

13. The apparatus as recited in claim 10, further comprising:

means sealably mounting said first part in said annular cavity of said first engine structure and for axial movement of said first part within said cavity relative to said first engine structure.

14. The apparatus as recited in claim 10, further comprising:

means for sealably mounting said second part in said annular cavity of said second engine structure.

15. The apparatus as recited in claim 10, wherein said secondary pressure balance means includes circumferentially-spaced non-intersecting pluralities of first and second conduits formed in said second part and extending generally in opposite diametric relationships across said second part from said end surface thereof toward an opposite end surface thereof.

16. The apparatus as recited in claim 15, wherein said secondary pressure balance means also includes radially-spaced non-intersecting pluralities of third and fourth conduits intersecting with said respective first and second conduits and extending and providing flow communication between said first and second conduits and opposite outer and inner annular surfaces of said second part.

17. The apparatus as recited in claim 16, wherein said first and second conduits extend to and open at said opposite end surface of said second part.

18. The apparatus as recited in claim 16, wherein said first and second conduits terminate midway across said second part where they intersect with said respective third and fourth conduits.

19. The apparatus as recited in claim 15, wherein said secondary pressure balance means also includes:

outer and inner annular compartments defined at said opposite end surface of said second part in flow communication with said annular cavity of said second engine structure;

said first and second conduits extending and providing flow communication between respective outer and inner grooves in said end surface of said first part and said inner and outer compartments at said opposite end surface of said second part.

20. The apparatus as recited in claim 19, wherein said outer and inner compartments are formed at said opposite end surface of said second part by a land structure projecting therefrom and contacting said second engine structure within said annular cavity thereof.