USRE48320EActiveUtilityPatentIndex 50
Gas turbine
Est. expirySep 6, 2033(~7.2 yrs left)· nominal 20-yr term from priority
F01D 11/12F05D 2260/36F05D 2240/11F05D 2230/70F05D 2220/3212F05D 2200/11Y10T29/49318F05D 2230/60F01D 25/246Y10T29/49233F05D 2230/68F01D 25/24Y10T29/49321F01D 11/127F01D 11/00F01D 11/08F05D 2260/37F01D 25/285F01D 11/122Y10T29/53983
50
PatentIndex Score
0
Cited by
8
References
15
Claims
Abstract
The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20i, 201+1), wherein a free axial path length (af) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a1) of a rotation locking member (10) of the outer sealing ring (af≥a1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a2) of a radial mounting rail (23) of the outer sealing ring (af≥a2), and/or an axial offset (a3, a4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit and pi is at least as large as a difference between a maximum outer diameter of the outer sealing ring and a minimum inner diameter of the flow channel inlet of the housing.
Claims
exact text as granted — not AI-modifiedWhat is claimed is:
1. An aircraft-engine gas turbine, having a housing that has a flow channel inlet, a first array of rotor blades in a direction of through-flow arranged in the housing, and an outer sealing ring for sealing the first array of rotor blades attached to the housing by a clamp in a friction fit, and the outer sealing ring comprising a plurality of ring segments; wherein
a free axial path length of each of the plurality of outer sealing ring segments counter to the direction of through-flow is at least as large as defined between a portion of the outer sealing ring and a portion of the housing, and
a quotient of a clearance sum
(
∑
i
=
1
n
u
i
)
of the outer sealing ring attached to the housing in a friction fit and pi (π) is at least as large as a difference between a maximum outer diameter (D 20 ) of the outer sealing ring, attached to the housing in a friction fit, and a minimum inner diameter (d 16 ) of the flow channel inlet of the housing
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,
wherein n is the number of the plurality of ring segments, and
wherein u i is a clearance or gap between adjacent ring segments of the plurality of ring segments in a peripheral direction.
2. The aircraft-engine gas turbine according to claim 1 , wherein a rotation locking member lock has a groove arrangement with at least one axial groove in the housing that is open counter to the direction of through-flow, in which a radial flange of the outer sealing ring attached to the housing in a friction fit engages in the peripheral direction in a form-fitting manner, and wherein the free axial path length of each of the plurality of outer sealing ring segments counter to the direction of through-flow is at least as large as a maximum groove length of the at least one groovearrangement.
3. The aircraft-engine gas turbine according to claim 1 , wherein the array of rotor blades has a first sealing fin and a second sealing fin, the second sealing fin is spaced apart axially from the first sealing fin, and the outer sealing ring has a first sealing face for sealing the first sealing fin and a second sealing face for sealing the second sealing fin, the second sealing face is spaced apart axially and radially from the first sealing face, and the free axial path length of each of the plurality of outer sealing ring segments counter to the direction of through-flow is at least as large as an axial offset of the first sealing fin with respect to a downstream edge of the first sealing face and at least as large as an axial offset of the second sealing fin with respect to a downstream edge of the second sealing face.
4. The aircraft-engine gas turbine according to claim 1 , wherein the maximum outer diameter of the outer sealing ring attached to the housing in a friction fit is larger than the minimum inner diameter of the flow channel inlet.
5. The aircraft-engine gas turbine according to claim 1 , wherein the array of rotor blades is configured and arranged to convert flow energy into mechanical work and/or or a flow channel outlet of the housing has a larger inner diameter than the flow channel inlet of the housing.
6. A method for dismounting an array of rotor blades of a gas turbine, comprising the steps of:
providing a housing that has a flow channel inlet, a first array of rotor blades in a direction of through-flow arranged in the housing, an outer sealing ring for sealing the first array of rotor blades attached to the housing by a clamp in a friction fit, and a plurality of ring segments; wherein
a free axial path length of each of the plurality of ring segments counter to the direction of through-flow is at least as large as
a quotient of a clearance sum
(
∑
i
=
1
n
u
i
)
of the outer sealing ring attached to the housing in a friction fit and pi (π) is at least as large as a difference between a maximum outer diameter of the outer sealing ring, attached to the housing in a friction fit, and a minimum inner diameter of the flow channel inlet of the housing
(
∑
i
=
1
n
u
i
≥
(
D
2
0
-
d
1
6
)
·
π
)
;
releasing the clamp;
withdrawing the plurality of ring segments of the outer sealing ring, as a whole set, from the housing counter to the direction of through-flow through the flow channel inlet; and
withdrawing the first array of rotor blades from the housing counter to the direction of through-flow through the flow channel inlet.
7. The method according to claim 6 , further comprising the steps of:
displacing the plurality of ring segments after release of the clamp, without any tilt and/or all together, axially counter to the direction of through-flow until a rotation locking member and/or a radial mounting rail is disengaged and/or a sealing fin is arranged downstream of a downstream edge; and/or displacing the plurality of ring segments radially inward until the maximum outer diameter is at most as large as the minimum inner diameter of the flow channel inlet.
8. The method according to claim 6 , further comprising the steps of:
inserting the first array of rotor blades into the housing in the direction of through-flow through the flow channel inlet; inserting the plurality of ring segments of the outer sealing ring into the housing in the direction of through-flow through the flow channel inlet; and attaching the clamp to the outer sealing ring.
9. The method according to claim 8 , wherein the plurality of ring segments are displaced, prior to the attachment of the clamp, without any tilt and/or all together, axially in the direction of through-flow until a rotation locking member and/or a radial mounting rail is engaged and/or a sealing fin is displaced with respect to an edge counter to the direction of through-flow; and/or are displaced radially outward until the maximum outer diameter is larger than the minimum inner diameter of the flow channel inlet.
10. The aircraft-engine gas turbine according to claim 1 , wherein the free axial path length of each of the plurality of outer sealing ring segments counter to the direction of through-flow is at least as large as an axial engagement of a rotation locking member of lock between the outer sealing ring, fit counter to the direction of through-flow and the housing.
11. The aircraft-engine gas turbine according to claim 1 , wherein the free axial path length of each of the plurality of outer sealing ring segments counter to the direction of through-flow is at least as large as an axial overhang of a radial mounting rail of the outer sealing ring.
12. The aircraft-engine gas turbine according to claim 1 , wherein the free axial path length of each of the plurality of outer sealing ring segments counter to the direction of through-flow is at least as large as an axial offset of a sealing fin of the outer sealing ring one rotor blade of the first array of rotor blades counter to the direction of through-flow with respect to a downstream edge of a sealing face of each of the plurality of ring segments for sealing of the sealing fin.
13. The method according to claim 6 , wherein the free axial path length of each of the plurality of ring segments counter to the direction of through-flow is at least as large as an axial engagement of a rotation locking member of the outer sealing ring, fit counter to the direction of through-flow.
14. The method according to claim 6 , wherein the free axial path length of each of the plurality of ring segments counter to the direction of through-flow is at least as large as an axial overhang of a radial mounting rail of the outer sealing ring.
15. The method according to claim 6 , wherein the free axial path length of each of the plurality of ring segments counter to the direction of through-flow is at least as large as an axial offset of a sealing fin of the outer sealing ring counter to the direction of through-flow with respect to a downstream edge of a sealing face of each of the plurality of ring segments for sealing of the sealing fin.Cited by (0)
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