Reduced leakage air seal

Patent metadata

Field	Value
Publication number	US-11028715-B2
Application number	US-201816149499-A
Country	US
Kind code	B2
Filing date	Oct 2, 2018
Priority date	Oct 2, 2018
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.

First claim

What is claimed is:

1. A reduced leakage seal for a gas turbine, comprising:
a control ring having a radially outward facing control surface and a radially inward facing control surface, the control ring having a thermal expansion time constant; the control ring coaxial with an axis;
an outer ring having a radially inward facing outer stator; the outer ring having a radially inward contact surface cooperating with the radially outward facing control surface limiting a radially inward position of the outer ring with respect to the control ring; the outer ring having a second thermal expansion time constant;
an inner ring having a radially outward facing inner stator, the inner ring having a radially outward contact surface cooperating with the radially inward facing control surface limiting a radially outward position of the inner ring with respect to the control ring; the inner ring having a third thermal expansion time constant;
a plurality of alignment restraints, the plurality of alignment restraints restricting axial translation of the control ring, the outer ring, and the inner ring with respect to one another; and
a rotating structure comprising an axially extending arm comprising a first set of outward facing knives and a second set of inward facing knives, wherein the outward facing knives are axially aligned and opposing the outer stator and the inward facing knives are axially aligned and opposing the inner stator, and wherein the axially extending arm at least in part separates a first volume and a second volume;
wherein the thermal expansion time constant of the control ring is greater than the second thermal expansion time constant of the outer ring.

2. The seal of claim 1 , wherein the first volume contains hot combustion gases.

3. The seal of claim 1 , wherein the thermal expansion time constant of the control ring is greater than or equal a thermal expansion time constant of the rotating structure.

4. The seal of claim 1 , wherein the outer ring comprises a first radially extending flange, the first radially extending flange in contact with at least one of the plurality of alignment restraints.

5. The seal of claim 1 , wherein the inner ring comprises a second radially extending flange, the second radially extending flange in contact with at least another of the plurality of alignment restraints.

6. The seal of claim 1 , wherein each of the control ring, the outer ring, and the inner ring are in contact with each of the others.

7. The seal of claim 1 , wherein the plurality of alignment restrains are selected from the group consisting of pins, brackets and clips.

8. The seal of claim 7 , wherein the pins comprise shoulder bolts.

9. A gas turbine engine comprising:
a rotor disk;
a hot zone containing combustion gases;
a cool zone containing cooling air, and a labyrinth seal separating the combustions gases from the cooling air in the cool zone;
the labyrinth seal comprising:
a control ring having a radially outward facing control surface and a radially inward facing control surface, wherein the control ring is coaxial with an axis, wherein the control ring has a first thermal expansion time constant;
an outer ring comprising a radially inward facing outer stator, wherein the outer ring has a radially inward contact surface cooperating with the radially outward facing control surface limiting a radially inward position of the outer ring with respect to the control ring; the outer ring having a second thermal expansion time constant;
an inner ring comprising a radially outward facing inner stator, wherein the inner ring has a radially outward contact surface cooperating with the radially inward facing control surface limiting a radially outward position of the inner ring with respect to the control ring, wherein the inner ring has a third thermal expansion time constant; and

a plurality of alignment restraints, wherein the plurality of alignment restraints restrict axial translation of the control ring, the outer ring, and the inner ring with respect to each other; and
a rotating structure comprising an axially extending arm comprising a first set of outward facing knives and a second set of inward facing knives, wherein the outward facing knives are axially aligned and opposing the outer stator and the inward facing knives are axially aligned and opposing the inner stator, and wherein the axially extending arm at least in part separates a first volume and a second volume;
wherein the first thermal expansion time constant of the control ring is greater than the second thermal expansion time constant of the outer ring.

10. The engine of claim 9 , wherein the control ring has an axial overlap with the first stator limiting a minimum radial position of the first stator with respect to the control ring.

11. The engine of claim 10 , wherein the control ring has a second axial overlap with the second stator limiting a maximum radial position of the second stator with a respect to the control ring.

12. The engine of claim 11 , wherein the axial overlap and the second axial overlap comprise a tab extending axially from the control ring.

13. The engine of claim 12 , wherein a plurality of pins maintains the control ring, the first stator, and the second stator concentric to a center axis of the turbine engine.

14. A method of controlling gaps between knives and stators in a labyrinth seal for a gas turbine engine comprising:
providing the labyrinth seal including:
a control ring having a radially outward facing control surface and a radially inward facing control surface, wherein the control ring has a first thermal expansion time constant; the control ring coaxial with an axis;
an outer ring having a radially inward facing outer stator, wherein the outer ring has a radially inward contact surface cooperating with the radially outward facing control surface limiting a radially inward position of the outer ring with respect to the control ring; the outer ring having a second thermal expansion time constant;
an inner ring having a radially outward facing inner stator, the inner ring having a radially outward contact surface cooperating with the radially inward facing control surface limiting a radially outward position of the inner ring with respect to the control ring; the inner ring having a third thermal expansion time constant;
a plurality of alignment restraints, the plurality of alignment restraints restricting axial translation of the control ring, the outer ring, and the inner ring with respect to one another; and
a rotating structure comprising an axially extending arm comprising a first set of outward facing knives and a second set of inward facing knives, wherein the outward facing knives are axially aligned and opposing the outer stator and the inward facing knives are axially aligned and opposing the inner stator, and wherein the axially extending arm at least in part separates a first volume and a second volume;
wherein the thermal expansion time constant of the control ring is greater than the second thermal expansion time constant of the outer ring;

varying a radius of the rotating structure associated with the labyrinth as a function of time, temperature and rotational speed of the rotating structure;
varying a radius of the control ring as a function of time and temperature;
limiting radial contraction of the outer ring as a function of the radius of the control ring during a first engine condition;
limiting radial expansion of the inner ring as a function of the radius of the control ring during a second engine condition;
wherein a first gap in the labyrinth seal is a function of the radius

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Dierksmeier Douglas David

Classifications

• F05D2240/55

  Seals · CPC title

• F05D2220/321

  for a special turbine stage · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D11/025 Primary

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title

• F01D9/04

  forming ring or sector · CPC title