U.S. patent number 3,807,891 [Application Number 05/289,496] was granted by the patent office on 1974-04-30 for thermal response turbine shroud.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to Ralph E. Bailey, Ferrell Holt, Robert W. McDow.
United States Patent |
3,807,891 |
McDow , et al. |
April 30, 1974 |
THERMAL RESPONSE TURBINE SHROUD
Abstract
In a turbine engine the vanes and shrouds around the turbine
blade tips are constructed to provide for radial positioning and
axial movement. The shroud for the first turbine stage includes a
growth control ring having a low expansion material while a high
expansion material is used for the shroud. In order to maintain the
desired temperature of the control ring, a heat shield is provided.
All of the cooling air for the first and second vane is routed
through the control ring. The second vane has a floating seal which
can grow outwardly against the inner platforms of the vane. The
invention described herein was made in the course of or under a
contract with the Department of the Army.
Inventors: |
McDow; Robert W. (North Palm
Beach, FL), Bailey; Ralph E. (Palm Beach Gardens, FL),
Holt; Ferrell (Oakridge, TN) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
23111788 |
Appl.
No.: |
05/289,496 |
Filed: |
September 15, 1972 |
Current U.S.
Class: |
415/116; 415/138;
415/173.1; 415/178; 415/134; 415/173.7; 415/209.1 |
Current CPC
Class: |
F01D
11/08 (20130101); F01D 9/042 (20130101) |
Current International
Class: |
F01D
9/04 (20060101); F01D 11/08 (20060101); F10l
005/00 (); F10l 005/08 (); F10l 025/28 () |
Field of
Search: |
;415/115,116,117,17R,217,216,134,136,178 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: McCarthy; Jack N.
Claims
We claim:
1. A turbine construction including a rotor having blades, a
thermal response shroud surrounding said blades, a ring means
surrounding said shroud, said shroud having arm means connecting
said shroud to said ring means, said ring means being made of a
material having a low coefficient of expansion, said shroud and
connecting means being formed of a material having a high
coefficient of expansion.
2. A turbine construction as set forth in claim 1 wherein said
connecting arm means comprises fingers extending outwardly from the
front and rear edges of the circumference of the shroud.
3. A turbine construction as set forth in claim 1 wherein said ring
means has an annular passageway therein, radial passage means in
said ring means connecting said annular passageway to the exterior
of said ring means, means for directing air to said radial passage
means, vane means located forwardly of said blades, conduit means
extending forwardly of said ring means through said arm means, said
conduit means being connected at one end to said annular
passageway, air from said conduit means being directed to said vane
means for cooling.
4. A turbine construction as set forth in claim 3 wherein said
connecting arm means comprises fingers extending outwardly from the
front and rear edges of the circumference of the shroud, and the
conduit means extends between the fingers.
5. A turbine construction as set forth in claim 2 wherein said arm
means has means connecting said shroud to said ring means for
limited axial movement of said shroud on said ring means, vane
means located forwardly of said blades, said vane means being
mounted for a limited axial movement with respect to said ring
means.
6. A turbine construction as set forth in claim 5 wherein said arm
means has axial extending flanges for radially spacing said shroud
and ring means, said flanges engaging grooves in said ring means,
said flanges of said arm means and the bottom of said ring means
being spaced so that a limited axial movement is provided
therbetween.
7. A turbine construction including a rotor having blades, a
thermal response shroud surrounding said blades, a ring means
surrounding and supporting said shroud, said ring means having an
annular passageway therein, radial passage means in said ring means
connecting said annular passageway to the exterior of said ring
means, means for directing air to said radial passage means, said
ring means having conduit means extending forwardly of said ring
means, said conduit means being connected at one end to said
annular passageway, vane means located forwardly of said blades,
air from said conduit means being directed to said vane means for
cooling.
8. A turbine construction as set forth in claim 7 wherein said vane
means and said thermal response shroud are mounted for limited
axial movement with respect to said ring means, said vane means
being axially guided on said conduit means.
9. A turbine construction as set forth in claim 8 wherein said vane
means has a wall means facing said ring means, said conduit means
being slidable in opening means in said wall means.
10. A turbine construction as set forth in claim 7 wherein second
vane means are located rearwardly of said blades, said ring means
having second conduit means extending rearwardly out of said ring
means, said second conduit means being connected at one end to said
annular passageway, air from said second conduit means being
directed to said second vane means for cooling.
11. A turbine construction as set forth in claim 10 wherein said
vane means located forwardly of said blades, said thermal response
shroud, and said second vane means located rearwardly of said
blades are permitted limited axial movement therebetween, said vane
means located forwardly of said blades being axially guided on said
conduit means extending forwardly of said ring means and said
second vane means located rearwardly of said blades being axially
guided on said second conduit means.
12. A turbine construction as set forth in claim 10 whereby said
conduit means extending forwardly out of said ring means has a
larger cross-sectional area than the second conduit means extending
rearwardly out of said ring means for permitting more air to flow
to said vane means located forwardly of said blades.
13. A turbine construction including an outer housing, said outer
housing having a ring means forming a part thereof and extending
inwardly from said housing, a thermal response shroud mounted on
said ring means, said thermal response shroud being permitted a
limited axial movement on said ring means, a rotor having blades
being mounted for rotation within said thermal response shroud, a
first vane means located forwardly of said blades being slidably
mounted in an axial direction within said turbine housing, a second
vane means located rearwardly of said blades being slidably mounted
in an axial direction within said turbine housing, said ring means
having a coolant passageway, therein, first conduit means extending
forwardly of said ring means with one end being connected to said
coolant passageway, a second conduit means extending rearwardly of
said ring means with one end being connected to said coolant
passageway, said first vane means being circumferentially
positioned by said first conduit means, second vane means being
circumferentially positioned by said second conduit means, each
conduit means directing coolant to its respective vane means.
Description
BACKGROUND OF THE INVENTION
This invention relates to turbine shrouds and more particularly to
those which are arranged to move in response to thermal changes to
maintain best turbine performance, this is a close tip clearance
during operation and a large tip clearance during shutdown and
operating transients. A sample of these are shown by U.S. Pat. Nos.
3,391,904; 2,859,934; and 3,443,791. A thermal response shroud is
also shown in U.S. Application Ser. No. 101,481 to Perry P. Sifford
filed Dec. 8, 1970 now U.S. Pat. 3,742,705.
SUMMARY OF THE INVENTION
A primary object of the present invention is to provide a thermal
response turbine shroud that will maintain the required radial
clearance for a turbine blade tip throughout the operating regime
of the engine with a minimum of variation.
In accordance with the present invention, this construction
provides close tip clearance when operating for best turbine
performance, a large tip clearance to prevent rotor seizure or rub
during shutdown and operating transients, a large build clearance
for ease of assembly, and good durability and life.
In accordance with a further aspect of the present invention a
growth control ring is provided of low expansion material while the
shroud is constructed of a high expansion material. The low
expansion control ring keeps the shrouds from growing outwardly and
the high expansion shroud fingers connected to the control ring
push back inwardly towards the blade tips to close the
clearance.
In accordance with another aspect of the present invention all of
the cooling air for the first and second vane is passed through the
blade control ring. This arrangement helps to maintain the desired
temperature at the control ring.
In this construction the vanes and shrouds are axially floating and
aerodynamically loaded against each other during engine operation
and transients to eliminate axial gap and control leakage between
vanes and shrouds.
The inner stage seal is mounted to permit radial movement with
respect to the second stage vanes.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a side elevation of a power plant showing the location of
the invention.
FIG. 2 is an enlarged view showing the turbine construction in
accordance with the present invention.
FIG. 3 is a view taken along the line 3--3 of FIG. 2.
FIG. 4 is another sectional view of the seal support in FIG. 3
showing a pin mounting.
FIG. 5 is a view taken along the line 5--5 of FIG. 4.
DESCRIPTION OF THE PREFERRED EMBODIMENT
In FIG. 1, a gas turbine power plant 1 is shown having an inlet 3
and exhaust section 5. The details of a similar power plant are
shown in U.S. Pat. No. 3,152,443. While the power plant as shown in
the patent is adapted to deliver power to a power shaft, and the
power plant herein provides thrust by a jet, this has no bearing on
the invention disclosed herein.
As shown in FIG. 2 the turbine section comprises three main parts:
(1) the turbine rotor means 7, (2) the composite outer turbine
housing 9, and (3) a thermal response turbine shroud 11. The
turbine rotor means 7 comprises two rotor discs 13 and 15,
supported for rotation within said power plant by bearing means not
shown. Turbine disc 13 has blades 17 mounted thereon and turbine
disc 15 has blades 19 mounted thereon. These blades can be
connected to the discs by any means desired. The turbine discs 13
and 15 are fixedly connected by a cylindrical member 20. Member 20
can be bolted to the discs or fixed by any other means desired.
Knife edges extend outwardly from the member 20 to provide a
sealing action to be later herein described.
The outer turbine housing 9 consists of four members which are
bolted together to form a rigid structure. These parts comprise the
forward nose section 24, a shroud support ring section 26, an
intermediate section 28, and a rear support section 30.
The shroud support ring section 26 is of annular construction
having an annular groove 32 around the inner circumference thereof,
said groove extends into said ring section for approximately one
half of its radial thickness, a plurality of openings 34 extend
through the forward part of the ring section between the groove 32
and the forward wall and a plurality of holes 36 extend through the
rearward part of the ring section between the groove 32 and the
rearward wall. The outer circumference of the ring section is
formed having projections 38 through which a plurality of
longitudinal openings 40 extend. Radial passages 42 connect the
bottom of the groove 32 to the outer circumference of the ring
section between the projections 38. A cylindrical member 44 is
fixed to the inner circumference of the ring section 26 closing the
inner opening of the groove 32.
The forward nose section 24 has an outwardly extending annular
flange 46 which is placed against an outer forward face of the
support ring section 26 and the intermediate section 28 has an
outwardly extending flange 48 at the forward end thereof which
abuts an outer rearward face of the support ring section 26.
Openings in these flanges 46 and 48 align with the openings 40 in
the outer circumference of the ring section and bolts 50 rigidly
hold these three sections together. The intermediate section 28 has
an outwardly extending flange 52 at its rear end and the rear
support section 30 has an outwardly extending flange 54 at its
forward end. These flanges are arranged to engage each other and
are bolted together by a plurality of bolts 56. An O-ring seal can
be provided between the flanges if necessary. The rear end of the
rear support section 30 is attached to fixed engine structure 58 by
a sheet metal strip 61 which axially positions the outer turbine
housing and a pin 60 prevents rotation. The forward part of the
forward nose section 24 has a rearwardly facing annular groove 25
for a purpose to be hereinafter described.
The thermal response turbine shroud 11 consists of four members
which are mounted within said outer turbine housing 9 for axial
movement therein. These parts comprise a forward first vane
supporting means 62, a shroud means 64 for the first stage blades
17, a second vane supporting means 66, and a shroud means 68 for
the second stage turbine blades 19. The shroud means 68 is formed
of eight segments and surrounds the tips of the blades 19. Each
segment has outwardly projecting radial fingers 70 and 72. Finger
70 has a rearwardly extending flange 74 and finger 72 has a
rearwardly extending annular flange 76. The rear flange 76 is
slidably located in a groove 78 which is formed in the rear support
section 30 and the forward flange 70 is slidably located in a
groove 80 which is formed in the intermediate section 28. A pin 82
is located in aligned openings in each side of the groove 80, a
notch in each flange 74 is axially aligned with its pin 82
permitting axial movement and restraining rotation between the
shroud means 68 and the intermediate section 28 and rear support
section 30.
The second vane supporting means 66 is comprised of a plurality of
segments. Each segment comprises an outer channel member 84, vane
86, and inner shroud member 88. The outer channel member 84
includes a forward side 85 which faces the shroud means 64 and a
rearward side 87 which faces the shroud means 68. A cover plate 89
connects the ends of sides 85 and 87. The inner shroud member 88 is
connected to a sealing means 90 located between the rotor discs 13
and 15. Sealing means 90 includes an annular member 92 with another
annular member 94 fixed thereto. Member 94 comprises a plurality of
outwardly extending projections 96 which are spaced so as to
enclose each of the knife edges 22 extending outwardly from the
member 20.
The sealing means 90 also includes an annular ring 98 having an
outwardly extending flange means 100. Flange means 100 consists of
an outwardly extending flange 103 and an outwardly extending flange
105 spaced therefrom. A flange 102 extends inwardly from each inner
shroud member 88. An annular member 104 is positioned around the
inner face of the inner shroud members 88 and has a flange 106
which extends outwardly along the flange 102. Flanges 103 and 105
are spaced to encompass flanges 106 and 102.
A pin member 107 extends from each flange 102 and is positioned in
a slot 109 located around the outer edge of flange 105. The slots
109 are equally spaced about the flange 105 and there is one for
each vane 86. The pin 107 can be fixed to its flange 102 by any
means desired. It is shown riveted in this construction. These pins
107 and grooves 109 permit for radial growth between the sealing
means 90 and the vanes 86. The annular member 104 is positioned by
pin member 111 which projects from the flange 103 and is guided in
a groove 113 formed in flange 106.
The shroud means 64 surrounds the tips of the blades 17 and
comprises a shroud face 110 facing the tips of the blade 17. This
face is formed on a plurality of arcuate segments 112 which are
fitted together around the blade tips. At the forward end of the
segments radial members or fingers 114 project outwardly therefrom,
each with a rearwardly projecting flange 116. A rear face extension
means 118 abuts the rearward end of the segments 112 and has radial
members or fingers 119 projecting radially outwardly having flange
means 120 at the outward end thereof which extend forwardly. The
flanges 116 and 120 extend into grooves 122 and 124 respectively to
position the shroud means 64. The rear face extension means 118 can
be fixed to the segments 112 by any means desired. A heat shield
means 121 is positioned against projections on the outer side of
the segments 112.
The forward first vane supporting means 62 is formed of a plurality
of segments. Each segment comprises an outer channel member 140,
vane 142, and an inner shroud member 144. Each inner shroud member
is mounted in an annular member 146 having an outwardly positioned
groove. The member 146 is pinned to inner fixed structure 150 to
permit axial movement and prevent rotation thereof and sealing
rings 152 are positioned in a groove 153 in the fixed structure and
engage the inner surface of the annular member 146. The outer
channel member 140 includes a rearward side 141 which faces the
shroud means 64 and a forward side 145 which has a projection 143
which is located in the groove 25. A cover plate 147 connects the
ends of sides 145 and 141.
The openings 34 and 36 have short pipe sections 126 and 128 mounted
therein, respectively. These pipe sections 126 and 128 pass between
the fingers 114 and 119, respectively and are slidably mounted in
openings 162 and 161, respectively, in the sides 141 and 85. The
pipe sections locate the vanes 142 and 86 and prevent relative
rotation therebetween and also prevent shroud 112 from
rotating.
In a construction built, the high expansion material was Haynes 188
and the low expansion material was NX 188.
* * * * *