Ge Xv-5a Manual

AUG

Book

No.

SPECIFICATION

NO.

124

INSTALLATION,

OPERATION

AND

o

MAINTENANCE

INSTRUCTIONS

r

FOR

X353-5B

AND

X376

FANS

,4

LIFT

FAN

FLIG

lACK

Al

FT

GRAM

CONTRACT

NUMBER

DA44-177-TC-715

WIIT

UTIN,

NFV

$ECTIOIE"

09RWCEN 1

,;..*

lIR.............................

..............

.

....................

G

E

N

E

R

A

L

E

LE

C

T

R

IC

iI

''-"

i R1I

I IMAR

E3d

DDC

AVAILABILITY

NOTICES

1.

Distribution

of

this

document

is

unlimited.

2.

This

document

is

subject

to

special

export

controls

and

each

trans-

mittal

to

foreign

governments

or

foreign

nationals may

be

made

only

with

prior

approval

of

US

Army

Aviation

Materiel

Laboratories,

Fort

Eustip,

Virginia

23604.

3. In

addition

to

security

requirements

which

must

be

met,

this

docu-

ment

is

subject

to

special

export

controls and

each

transmittal

to

foreign

governments

or

foreign

nationals may

be

made

only

with

prior

approval

of

USAAVLABS,

Fort Eustis,

Virginia

23604.

4.

Each

transmittal

of

this

document outside

the

agencies of

the

US

Government

mt~st

have

prior

approval

of

US

Army

Aviation Materiel

Laboratories,

Fort

Eustis,

Virginia

23604.

5. In

addition

to

security

requirements

which

apply

to

this

document

and

must

be

met,

each

transmittal

outside

the

agencies

of

the

US Government

must

have

prior

approval

of

US

Army

Aviation Materiel

Laboratories,

Fort

Eustis,

Virginia

23604.

6.

Each

transmittal

of

this

document outside

the

Department

of

Defense

must have prior

approval

of

US

Army

Aviation Materiel

Laboratories,

Fort

Eustis,

Virginia.

23604.

7. In

addition

to

security

requirements

which

apply

to

this

document

and

must

be

met, each

transmittal

outside

the

Department

of

Defense must have

prior

approval

of

US

Army

Aviation Materiel

Laboratories,

Fort

Eustis,

Virginia

23604.

8.

This document

may

be

further

distributed

by

any

holder

only

with

specific

prior

approval

of

US

Army

Aviation

Materiel

Laboratories,

Fort

Eustis,

Virginia

23604.

9.

In

addition

to

security

requirements

which

apply

to

this

document

and

must

be

met,

it

may

be further

distributed

by

the

holder

only

with

specific

prior

approval

of

US

Army

Aviation Materiel

Laboratories,

Fort

Eustis,

Virginia

23604.

DISCLAIMER

The findings

in

this

report

are

not

to

be

construed

as

an

official

Dep-ment

of

the

Army

position

unless

so

designated

by

other

authorized

documents.

When

Government drawings, specifications,

or

other

data

are

used

for

au

n

se

other

than

in

connedtion

with

a

definitely

procurement operation,

the

United

States

Government

thereby incurs

no

responsi-

bility

nor

any

obligation whatsoever;

and

the fact

that

the

Government

may

have formulated, furnished,

or in

any

way

supplied

the

said

drawings,

speci-

fications,

or

other

data

is

nvL

to

be

regarded

by

implication

or

otherwise

as

+*

---__ -....

*

,,1

TALE

OF

CONTENTS

PAGE

SECTION

1.

INTRODUCTION

................... 1

1.1

GENERAL

................

.. .. ... *.................... .

-i

1.2

SCOPE

.....

..

....................

... .......... .

.....

.. -1,1

1.3

REPLACEMENT

OF

PARTS

....................... .......

I-.1

SECTION

2.

SYSTEM DESCRIPTION

............................. .....

1-2.1

2

1

GENERAL

,

.. . . ..........

.*

.......... .

1-2.

1

2.2

BASIC

FAN

DESCRIPTION

.......................... * ... .......

1-2.1

2.3

SYSTEM ORIENTATION

.......................

.....

#

............

1-2.3

2.4

ROTOR

COMPONENT

DESCRIPTION

...............................

1-2.4

2.5

Shaft

and

Disc ...................

0

,

..... ...... .. ......

1-2.4

2.6

Blade Retainer

Rings

.....................

o

............

1-2.4

2.7

Rotor

Blades

.......................

..

....

...

1-2.4

2.8

Blade Platforms .................................

o

........

.

1-2.5

2.9

Torque

Band

Segments

..--.................

.....

..

1-2.5

2.10

Carrier

Segment

Seal

.....................................

1-2.5

2.11

Blade Shroud

Cover ........................................

1-2.6

2.12

.3lade

Carrier

Pins.

...................................

..

1-2.5

2.13

Lock

..................................................

..

1-2.6

2.14

Lock

Strip

...........

#.......

............

0...........

0........

1-2.6

2.15

Turbine

Bucket Carrier

Assembly

.........................

1-2.7

2.16

Turbine Buckets

...................... .........

#

......

1-2.7

2.17

Bucket Tip Shrouds

................... ............. ........

1-2.7

2.18

Bucket Caryier

...

. ...................

...

1-2.7

2.19

Bucket

Carrier

Tabs

.................................

.....

1-2.8

2.20

Balance

Weight

.

........

...

..................

1-2.8

2.21

Tie

Bolts,

Washers and

Nuts

.... ... ................

1-2.8

2.22

FRONT

FRAME

DESCRIPTION

.. ...... ......... ..................

1-2.9

2.23

Hub

............................... .....

....

...

..

......

1-2.9

2.24

Housing

-

Roller Bearing

....... o....... o.....

pit*

... .i-2.10

2.25

Bearing

System

.............. o

......... ......... o....

1-2.10

I-i

PAGE

2.26

Grease

Seals ..................................

*9*9

9 1-211

2.7I

-2.

1

2.27

Retainer

Seal

-

Ball

Bearing.......121

2.28

Grease

Shield

-

Ball

Bearing

.......

1-2.11

2.29

Retiiner-

Roller

Bearing

1-2.12

2.30

Grease Shield- Roller

Bearing

.....

........

-2.12

2.31

Boss-

Speed

Picek-up

Sensor

1 - 2 . 1 2

2.32

Magnetic

Rotor

Speed

Pick-up

Sensor

..........

.....

1-2.12

2.33

Struts

I.................

................ ...............

1-2.12

2.34

Bellmouth

...........

.

.....

... ....

.................

1-2.14

2.35

-

Support

Beam

........................................

1-2.15

2.36

Clevis

-

Scroll

Mounting..................................

1-2.15

2.37

Shoulder

Bolt

-

Scroll

Mounting...........................

1-2.15

2.38

Shim

-

Scroll

Mounting

Clevis

......

1-2.15

2.39

Forward Compressor

Seal

....

1-2.16

2.40

Insulation

Blanket

........... .

so,

1-2.16

2.41

INLET

VANE

DESCRIPTION

......

I....o....

1-2.17

2.42

SCROLL DESCRIPTION

99.99.99.... o

...

.......

-2.19

2.43

REAR

FRAME

.........

.....

@

....

...............

#

...

1-2.22

2.44

HONEYCOMB AIR

SEALS

................ * ... .............

1-2.24

2.45

TURNBUCKLE

-

REAR

FRAME

TO

SCROLL

1-2.25

2.46

INSULATION

BLANKET

-

INNER

............. *9

.....

99

.....

o *

*

1-2.25

2.47

INSULATION

BLANKET

-

OUTER

I

.. ....

9

1-2.25

2.48

EXIT LOUVER SYSTEM

.......... ...

T-2.25

249

Exit

Louvers

..................

*so

.......

*

..

99999.994.9

1-2.26

2.50

Actuator

Linkage

I...

.. ... *9 499999

999*

.......

1-2.27

2.51

DIVERTER

VALVE

DESCRIPTION

1-2.41

SECTION

3.

SPECIAL TOOLS

I..........

...999 ...

1-3.1

3

.1

GENERAL

I

-3.1

3.2

BEARING,

BALL,

INNER

RACE

........

.

1-3.1

3.3

BEARING,

BALL,

OUTER

RACE

.99999999999

1-3.1

3

.4

BEARING,

ROLLER,

INNER

RACE

...... ........ .

1-3

.2

3.5

BEARING,

ROLLER,

OUTER

RACE

I.............

...............

1-3.2

I-i

i

PAGE

3.6

EXIT

LOUVERS

......................

1-3.2

3.7

FRONT

FRAME

AND

SCROLL

.I..*..................*.......

1-3.2

3.8

LIFT

FAN

........

...................................

1-3.2

3

9

REAR

FRAm,

............

#

........

.

.............

.. . .*.

I-3

2

3.10

ROTOR...............

..

.............

1-3.3

3.11

TURBINE

BUCKET

CARRIER SEGMENT

.

.......................

1-3.3

3.12

NUMERICAL TOOL LIST

.. .

..

......

.................

1-3.4

SECTION

4.

ASSEMBLY

OF

X353-5B

........................

....

1-4.1

4.1

GENERAL

ASSEMBLY

PROCEDURE

.... .........

#

..............

1-4

.1

4.2

Scope

.I..... ...

......

.....*..

.....

..... .

*.

1-4.1

4.3

ASSEMBLY

TOOLING

....................

.... ....

1-4.1

4.4

ROTOR

ASSEMBLY

(REFERENCE FIGURE

4.2)

.................

1-4.2

4.5

Disc

and

Shaft Assembly.

0.0.0

..

1-4.2

4.8

Assembly

of

Rear

Blade

Retainer Ring

......................

1-4.4

4.9

Assembly

of

Blade

Platforms

.......

I......0..............

1-4.4

4.10

Assembly

of

Torque

Band

Segments ..........................

1-4.4

-.

4.11

Assembly

of

Carrier

Seals

...............................

1-4.5

4.12

Assembly

of

Bucket Carrier Segments

...................

1-4.6

4.13

BAI.ANCE

PROCEDURE

I..............o...

1-4.8

4.14

TOhOUINGPROCEDURE

.............

... ..

*.

.............

.o..

1-4.9

4.15

.9

1ADIAL

INSPECTION

..................

I-4.11

4.16

FRONT

FRAMZ

ASSEMBLY

..........

. .

.........

.

1-4.11

4

J7

ORIENTATION

.................

t....

* o.,

.........

1-4.11

4.18

ASSEMBLE

INSULATION

BLANKET

I.......................

1-4.11

4.19

ASSEMBLY

OF

810

SCROLL

MOUNTS

..........................

1-4.12

4.20

SCROLL

ASSEMBLY

...................

. ... ..

to

1-4.13

4.21

Inspection

and

Adjustment

of

the

Scroll

to

the

Front

Frame

............. ..........

-4.15

4.22

Assembly

of

Scroll

Finger

Seals

I....................

1-4.16

4.23

Assembly

of

Scroll

Insulation

.......................

1-4.17

4.24 Final

Assembly

of

Scroll

to

Front Frame

...................

1-4.17

4.25

Assemble Scroll

Seals and

Air

Seal

Supports

...............

1-4.17

'-iii

PAGE

4.26

Assemble Honeycomb

Air

Seal

.........

........

1-4.18

4.27

Assembly

of

Thrust

Bearing

Outer

Race .....................

1-4.18

4.28

Assemble

Rear

Frame

Insulation

Blankets

...................

1-4.19

4.29

Assembly

of

Rear

Frame

Air

Seal

Segments

..................

1-4.20

4.30

Assemble Rotor

to

Front

Frame and

Scroll

..........

1.......

-4.21

4.31

Assemble

Bearing

Inner

Races

to

Rotor

Shaft

...............

1-4.21

4.32

Assemble

the

Rotor

to

the

Thrust

Bearing

..................

1-4.22

4.33

Assemble

the

Roller

Bearing

.........................

1-4.23

4.34

Clearance Inspection

Prior

to

Assembly

of

Rear

Frame

......

1-4.24

4.35

Assembly

of

Rear

Frame

to

Front

Frame

.....................

1-4.25

4.36

Clearance

Inspection

after

Assembly

of

Rear

Frame

.........

1-4.26

4.37

Assemble

and

Adjust

Magnetic

Speed

Pickup

.........

00#......

1-4.27

4.38

Setting

of

Nozzle

Area

Adjustment

Vanes ...................

1-4.27

4.39

EXIT

LOUVER

ASSEMBLY

.

1-4.28

4.40

Orientation

of

the

Exit

Louver

Push

Rods

..................

1-4.28

4.41

Assembly

of

Exit

Louver

Push

Pods

1-4.29

4.42

Assemble

Bushings

to

Supports

......................

1-4.29

4.43

Assemble

Louver Port

Bushing

to

Strut

.....................

1-4.29

4.44

Assemble

the

Lever

Arms

to

Louvers

................

.....

1-4.30

4.45

Assemble

Exit

Louver

#14

...................

..

1-4.30

4.46

Assemble

Louver

#38

.... ..

&

.......

..... ...

1-4.31

4.47

Assemble

Louver

#13

...............

. ....

......

.

1-4.31

4.48

Assemble Louver

#15

.................

...........

.

1-4.31

4.49

Assembly

of

Remaining

Louvers

........................

1-4.31

4.50

ASSEMBLY

OF

CIRCULAR

VANE

...............

.....

..

........

1-4.32

4.51

DIVERTER VALVE ASSEMBLY

....................................

1-4.107

4.52

GENERAL

.................................... #.......#........

1-4.107

4.53

ASSEMBLE INSULATION

BLANKET

...............................

1-4.107

4.54

ASSEMBLE

DOORS

............

.

.......... .

..

................

1-4.107

4.55

Assemble

Seals

Springs,

Seal

Segments

and

Tube

Seals

......

1-4.107

4.56

Assemble

Doors

to

Valve

Body

..............................

1-4.108

4.57

ASSEMBLE

DIFFUSER

CONE

................

*

.................

1-4.109

4.58 INSPECTION

...............

.....

.........

1-4.109

I-iv

PAGE

4.9

AO-4

4.59

ASSEMBLE ACTUATOR

LINKAGE

...........

..........

1-4.109

4

60ASSEMBLE

ACTUATOR

IU*~**~*******~*******

-4.110

4.61

ASSEMBLE

DOOR

LIMIT

SWITCHES

..............................

1-4.111

4.62

Assemble

Diverter

Valve

to

J85-5

1ngine

...................

1-4.112

4.63

Disassembly

of

Actuator

.....................

.. ......

1-4.113

4.64

Assembly

.. . ....... . . .o. . Ioo.

... . . .

-4.113

4.65

Actuator

Pressure Test

..................... .............

1-4.114

4.66

Diverter

Valve

Coupling

Description

I...............

1-4.114

4.67

Divertor

Valve

Splined

Torque

Shaft

Assmnbly

.............

1-4.115

4.68

Diverter

Valve

Coupling Assembly

o..............

.. 1-4.115

SECTION

5.

INSTALLATION

....

o

....

o.

......

................

1-5.1

5.1

INDUCTION

SYSTEM

...........

... ........ .. . ... ..o. ...

1-5.1

5.2

General

.. . . .. . . . . . .. .I0. . .0. . -5.1

5.3

Inlet

Closure

.... o.............

......

.....

**... ..

1-5.1

5.4

Inlet

Seal

.

1-5.2

5o5

Inlet

Connection

.. I....

...

.....

~o....

-5.2

SECTION

6.

X353-5B

LIFT

FAN DISASSEMBLY

1-6.1

6.1

PREPARATION

FOR

TEARDOWN

. ......... o.............. o.

....

1-6.1

6.2

REMOVE REAR FRAME

........... . ... .s

.o. . .

...

1-6.1

6.3

REMOVE

ROTOR FROM FRONT

FRAME...........................

I-6.1

6.4

REMOVE

SCROLL

FROM

FRONT

FRAME

.................

*..so.....

1-6.2

6.5

DISASSEMBLE

FRONT

FRAME

......................

1-6.2

6.6

Remove Circular

Vane

o.. . . . ... ............

1-6.2

6.7

Remove

Thrust Bearing Outer

Race

...

1-6.2

6.8

Remove

the

Roller Bearing

.............. I..............6.

1-6.3

6.9

Remove

the

Insulation

Blanket

I...............

1-6.3

6.10

Remove

Scroll

End

Clevises

..........

I..0.

...

0....

...

1-6.3

6.11

Remove

Speed Pick-up Bushing

.....

I.so

.......

...... I-6.3

6.12

DISASSEMBLE

ROTOR

o.......... ......... ,....

1-6.3

6.13

Remove

Carrier

Segments

.....

. .. . . .o. ....... ......

1-6.3

I-V

PAGE

6.14

Disassemble

Blades

........................................

...

......

1-6.4

6.15

Disassemble Bearings

..............

1-6.4

6.16

DISASSEMBLE

REAR

FRAME

.............. ...

*.

................

...

1-6.4

6.17

Remove Exit

Louvers

............................ ...........

1-6.4

6.18

Remove

Push

Rods

................. 0. ............... .

....

1-6.5

6.19

Remove Insulation

Blanket ................................

1-6.5

6.20

Remcve

Air

Seals

..............................

...

1-6.5

6.21

DISASSEMBLE

DIVERTER

VALVE

.......

...........

1-6.6

6.22

Actuation

Removal

............................

....... .

1-6.6

6.23

Door

Removal

.............................

.........

.

... .

1-6.6

6.24

Insulation

Blanket

Removal

..............

...

........

1-6.6

6.25

Diffuser

Removal

....................

....

...

..........

1-6.6

SECTION

7.

INSPECTION,

REPAIR

AND

REPLACEMENT

...................

1-7.1

7.1

GENERAL .......................................

..........

1-7.1

7.2

CLEANING

AND

INSPECTION

...................... ........

1-7.1

7.3

Cleaning

of

Bearings

....

................

,

.................

1-7.1

7.4

Fluorescent-Penetrant Method

of

Inspection

(Zyglo)

........

1-7.3

7.5

General

.............................. ....................

1-7.3

7.6

Cleaning Prior

to

Application

of

Fluoreqcent-Penetrant

....

1-7.3

7.7

Application

of

Fluorescent-Penetrant

(,il

..................

1-7.3

7.8

Application

of

Developer

.................................

1-7.3

7.9

BLADE TANG

AND

BLADE/DISC

DOVETAIL

COATING

................

1-7.4

7.10

PERIODIC

INSPECTION

REQUIREMENTS

..........................

1-7.32

7.11

LIFT

FAN

SERIAL

NUMBERS

................................

1-7.33

SECTION

8.

TESTING AFTER OVERHAUL

OR

MAINTENANCE

................

1-8.1

8.1

GENERAL

.........

.............. .

.........

..

............

1-8.1

SECTION

9.

OPERATION

OF

X353-5B PROPULSION SYSTEM

..........

1-9.1

9.1

GENERAL

............................. .......... ...

....

.

I-9.1

I-vi

LIST

OF

ILLUSTRATIONS

FIGURE

TITLE PAGE

1.1

X353-5B

Propulsion

System...............

1-1.2

2.1

Typical

Fan-In-Wing

X353-5B

Installation

............... 1-2.28

2.2

Major

Components

of

X353-SB

Lift

Fan

System

............

1-2.29

2.3

System Orientation

.................... ........

..

1-2.30

2.4

Lift

Fan Rotor

Component

..........

1-2.31

2.5

Lift

Fan

Front

Frame

............................

.

1-2.32

2.6

Lift

Fan

Assembly

Showing

Inlet

Vane

..............

t....

1-2.33

2.7

Lift Fan Scroll,

View

of

Inlet

.....................

1-2.34

2.8

Lift

Fan

Scroll,

View

of.Nozzle

............

....

1-2.35

2.9

Lift

Fan

Scroll,

ToP

View

...................

1-2.36

2.10

Sketch

of

Turbine

Nozzle

Partitions

..................

1-2.37

2.11

Scroll

Area

Adjustment

Mechanism

1-2.38

2.12

Lift

Fan

Rear

Fra:ae

............... .. ..o... ......... 1-

2.39

2.13

Exit

Louver

System

i.

.......

-2.40

2.14

Diverter

Valve

Asse~nb

.............

1-2.45

2.15

Diverter

Valve

Actuation

System......

I-2.46

2.16

Sketch

of

Actuation Linkage

in

Straight-Through

and

Diverted

Positions

I...

1-2.47

3.1

Rotor Balance

Arbor

1-3.5

3.2

Rotor Turnover

Dolly

.

I-3.5

3.3

Front

Frame,

Scroll

and-Fan

Turnover

Dolly

.....

*

......

1-3.6

3.4

Ball

Bearing

Inner

Race

Puller

1-3.6

3.5

Rotor

Vertical

Lift Fixture

...... ....

1-3.7

3.6

Roller

Bearing

Inner

Race

Puller

1-3.7

3.7

Spanner

Wrench

.............................

......

1-3

.8

3.8

Ball

Bearing

Outer

Race

Puller

1-3.8

3.9

Roller

Bearing

Outer

Race

Puller

..................

1-3.9

3.10

Tab

Bender,

Front

Frame and

Bearing

Assembly

...........

1-3.9

3.11

Lift

Fan

Shipping

Container

..

1-3.10

3.12

Lift

Fan

Transportation

Dolly

..........................

1-3.10

3.13

Front

Frame

and Scroll

Lift

Fixture

...................

1-3.11

0

I-vi

FIGURE

TITLE

PAGE

3.14

Rotor Support

Stand

.....

* .......

..........

1-3.11

3.15

Rotor

Balance

and Inspection Stand

...........

1-3.12

3.16

Front Frame Air

Seal

Grinding

(lift)

and

Inspection (Right) Fixtures

............................

1-3.12

,3.17

Carrier Retaining

Inserting

and

Removal

Tool

(Tool

for

Left Hand

Carriers

on

Left;

Tool

for

Right Hand

Carriers

on

Right)

*.........................

1-3.13

3:18 Exit Louver

Protractor

................................

13.13

3.19

Bearing

Cage

Support

...................................

1-3.13

3.20

Exit Louver

Template

.....

*

........

*..

I-S.14

4.0

Balance

Plot

-Top

Looking

Down........................

1-4.9

4.1

Lift

Fan Basic Assembly Drawing

(Left) "..

......

14.49

4.2

Lift Fan

Rotor

Assembly

Drawing

(Left)

.................

1-4.53

4.1A Lift Fan

Basic

Assembly

Drawing

(Right)

.................

1-4.71

4.2A Lift Fan

Rotor

Assembly

Drawing

(Right)

................ 1-4.75

4.2B

X353-5B

Lift Fan

Configuration

(left)

.................

1-4.76

4.2C

X353-5B

Lift

Fan

Installation

.................

1-4.79

4.3

Rotor

Tie

Bolt

Torquing

Procedure

.....................

1-4.83

4,4

Rotor Air

Seal

and

Tip

Seal

Inspection

................

1-4.84

4.5

Front

Frame Insulation

Blanket

Inspection

..............

1-4.85

4.6

Inspection

and

Adjustment

of

Scroll

to

Front

Frame

.....

1-4.96

4.7

Insepction

of

Scroll

to

Front Frame

............

0.......

1-4.87

4.8

Inspection and

Adjustment

of

Scroll

Center

Mount

Uniba!

Slot

.................... . . . I-4.88

4.9

Inspection and

Adjustment

of

Scroll

Seal

Overlap

.... ,..

1-4.89

4.10

Honeycomb

Ar

Seal

Attachment

.............

1-4.90

4.11

Honeycomb

Seal

Grinding

Instructions

and

Inspections

... 1-4.91

4.12

Rear Frame

Assembly

Drawing (Left Hand)

................

1-4.93

4.12A

Rear

Frame

Assembly Drawing

(Right

Hand)

............... 1-4.95

4.13

Inspection

of

Rear

Frame

Insulation

Blanket

Radius

.....

1-4.97

4.14

Assembly

of

Bearing

Retaining Nut Tabwasher

............

1-4.98

4.15

Inspection

of

Rotor

Axial

Clearances

.......

1-4.99

4.16A

Reference

Sketch

for

Final

Inspection

of

Assembly

......

1-4.1n

4.16B Rotor

Bearing

and

Speed

Sensor Clearance

Inspection

....

1-4.101

I-viii

FIGURE TITLE

PAGE

.4.16C

Rotor

Running Clearance

Inspection

............

....

1-4.102

4.17

Assembly

of

Adjustment

Lever

to

Louver

End

............

1-4.103

4.18

Inspection

of

Louver

Angle

Settings

............

1-4.104

4.19A

Torquing

Procedure

for

Torque

Band

Bolts,

(Right

H

and

Fan)

.. ..................................

1-4.105

4.19B

TorquiLng

Procedure

for

Torque

Band

Bolts,

(Left

H

and

Fan).................................

...........

1-4.106

4.20

Assembly

Drawing,

LeftHand

Diverter Valve

........

1-4.123

4.20A

Assembly

Drawing,

Right

Hand

Diverter

Valve...............1-4.131

4.21

Assembly

D

awing,

Diverter

Valve

Actuation

System.........1-4.133

4.21A

X353-5B Diverter

Valve

Installation.......................1-4.135

4.22

Diverter

Valve

Actuator...................................1-4.137

4.23

Exit

Louver

Actuation

Limits............................

1-4.138

4.24

Assembly

Drawing,

Coupled Diverter

Valves

(401200).

-

915)...........................................

1-4.139

.1Exit

Louver

System

................................

1-5.4

5.2

X353-5B

Fan Exit

Louver

Interference.................

1-5.5

5.3

X353-5B

Left

Hand

Fan

Mount

Reactions

..............

1-5.6

9.1

X353-5B

System

Installation

.....................

1-9.3

I-ix

SECTION

1.

INTRODUCTION

1.1

GENERAL

a.

This

publication,

prepared

by

the

General

Electric Company

in-

cludes

installation,

operation

and

maintenance

instructions

for

the

X353-5B

convertible

V/STOL propulsion

system.

This

propulsion

system

is

designed

and

manufactured

by the

General

Electric

Company,

Advanced

Engine

and

Technology

Department,

Evendale,

Ohio.

1.2

SCOPE

a.

The

X353-5B

propulsion

system

(Figure

l.l!consists

of

a

J85-GE-5

turbojet engine

(less

afterburner)

used

as

a

gas

generator,

a

diverter

valve

to

direct

the

gas

flow, and

an

X353-5B

lift fan

equipped

with

vectorable

dis-

charge

louvers.

Reference

to

the

J85

in

this

publication

will

be

limited

to

special

requirements

of

the

X353-5B

propulsion system.

Additional information

on

the

J85

engine

can

be

obtained

from

the

Small

Aircraft

Engine Department,

General

Electric

Company, Lynn,

Massachusetts.

1.3

REPLACEMENT

OF.

PARTS

a.

Only

General

Electric

Class

I,

Ia,

II

or

Ha

parts

are

acceptable

Ifor

use

in

any

X353-5B

propulsion

system.

Replacement parts

can

be

obtained

only

through

the

General

Electric

Company.

Inquiries

should

be

directed

to:

General

Electric

Company

Advanced Engine

and

Technology

Department

•Lift'Fan

Systems

Operation

Building

501

Cincinnati,

Ohio

45215

I-1.1

R-1

FIGURE

1.1

X353-5B PROPULSION

SYSTM

SECTION

2.

SYSTEM

DESCRIPTION

2.1

GENERAL

a.

The

X353-5B

lift

fan

is

designed

for

installation

in

the

wings

of

an

airplane

(Figure

2.1)

and

combines

desirable

VTOL

features

of

high

thrust,

low

sfc,

low

exhaust

velocities,

low

noise

levels and

low

weight.

It

is

a

convertible system

which

augments

the

thrust

of

a

turbojet

engine

for

vertical

takeoff

and

landing.

b.

The

J85

turbojet

engine

and

the lift fan

are

pneumatically

coupled

by

the

diverter valve

and

additional

ducting

as

may

be

required

for

a

specific

installation.

For

vertical

flight,

the

diverter

valve

deflects

exhaust gases

from

the

turbojet

into

a

tip

turbine

which

drives

the lift

fan.

During transition

from

hover

to

horizontal

flight,

louvers located

on

the

lower

surface of

the

fan

vector

the fan

exhaust

rearward

to

provide

horizontal

thrust

for

forward

acceleration.

Once

the

aircraft

has

reached

a

speed sufficient

for

wing

supported

flight,

the

diverter

valve

is

moved

to

the

straight-through position,

the

exit

louvers

and

the

wing

surface

over

the fan

inlet

are

closed

and

the

J85

turbojet

operates

in

a

conventional

manner.

2.2

BASIC

FAN

DESCRIPTION

a.

The

X353-5B

is

a

light-weight,

high-performance,

compact

V/STOL

lift

fan

propulsion system. The

major components

(Figure

2.2)

include

a

diverter

valve,

a

single-stage

axial

flow

fan,

a

power turbine

attached

to

the fan

blade

tips,

a

front

frame

with

an

inlet

guide

vane

assembly,

a

rear frame

containing

the

fan

and

turbine

exit

stator,

a

scroll

which

con-

tains

the

partial

admission

turbine

nozzle,

and

exit

louvers

supported

irom

the

rear

frame.

The

leading

system particulars

are

listed

in

Table

2.1.

1-2.1

R-2

TABLE

2.

1

X353-5B

LEADING

PARTICULARS

I.

LIFT

FAN

Type

Tip

turbine

lift

fan

Type

of

compressor Single-stage,

co-axial

flow

Type

of

Turbine

Single-stage,

impulse, partial

admission.

Fastened

to

blades

of

co-axial

fan.

Direction

of

rotation Clockwise

or

counter-clockwise.

Rotor

speed

(maximum)

2719

RPM

(103%)

Installed dimension:

Distance

between

82.5

inches

(cold)

wing

spar

centerline

Overall

dimension

89.1

inches

(cold)

(spanwise)

Fan

tip

diameter

62.5

inches

Depth

at

hub

18.2

inches

Depth

at

edge

14.40

inches

maximum

Weight

(maximum)

915

pounds (includes

instrumentation)

Center

of

gravity

The

lift

fan

C.G.

is

located

5.3"

from

fan

rotating

axis

on

minor

strut

centerline

and

vertically

0.62"

above

rotor

centerline.

Mounting

Three

Point.

At

leading

edge,

trailing

edge and

inboard

between

scroll

inlets.

2.

DIVERTER VALVE

Type

Tee,

with

double

"butterfly"

doors

Basic

length

34.8 inches

Basic

width

18

inches

between mounts,

16.5

inches

I.D.

Weight

(maximum)

91

pounds (includes

instrumentation)

Center

of

gravity

2.7

inches

forward

of

main

mounts,

4

inches

below

centerline.

Mounting

Integral with

gas

generator

1-2.2

R-2

TABLE

2.1

(Continued)

X353-SB LEADING

SYSTEM

PARTICULARS

3.

LUBRICATION

Fan

bearing grease

Texaco

Unitemp

500

oz

equivalent.

Grease

capacity

Ball

thrust

bearing

60

grams

Roller bearing

40

grams

Bearing temperatures

3500F

maximum

4.

ACCESSORIES

RPM

indicating

Magnetic reluctance

RPM

transmitter

RPM

to

DC

converter

5-1/4"

x 9"

5-3/4"

transistorized

instrument

package.

24-28

V.

DC,

2a.

Diverter

valve

position Terminal

position micro

switches.

transmitters

28

V.

DC

5

Amp.

resistive

2

Amp.

inductive

Diverter

valve

actuator

Two-position,

dual

piston.

Hydraulic

fluid

MIL-H-5606,

3000

psi,

2.7

gpm

(150

strokes/min.).

Design

stroke

3.85

in.,

max.

temperature

3000F.

2.3

SYSTEM

ORIENTATION

a.

Location

references

used

in

this

text

are

shown

in

Figure

2.3.

Similar

components

located

on

a

common

diameter around

the fan

are

numbered

clockwise starting from

the

12

o'clock

position.

The

12

o'clock position

is

the

forward point

of the fan

in

relation

to

the

nose

of the

aircraft;

this

point

remains

12

o'clock

regardless

of

the

direction

of

fan

rotation.

The direction

of

fan

may

be

either right

(clockwise)

or

left

(counter-

clockwise)

when viewing

the

rotor

from

the

top

looking

down.

The

symbol

L

(left)

or

R

(right)

after

the

fan

assembly

serial

number

identifies

the

direction

of

rotation.

References

to

the

forward

end

of

the lift

fan

pertain

to

the

inlet

or

top

side;

references

to

the aft end

of

the lift fan

pertain

to

the

exit

or

bottom

side.

1-2.3

R-2

-.. ... ._

_ _ _ _ _ _

_

__....... .

_

__.....

. . .. .. .. -----

2.4

ROTOR

COMPONENT

DESCRIPTION

a.

The

fan

rotor

component

(Figure

2.4)

is

a

single-stage,

axial

flow

compressor

which

pumps

air

downward

to

produce

lift.

The

rotor

consists

of

a

shaft

and

disc,

retainer

rings,

blades, blade

platforms,

torque

band

seals,

blade

shroud

covers,

blade

carrier pins,

a

carrier

assembly

which

includes

turbine

buckets,

and

carrier

tabs.

2.5

Shaft

and

Disc

a.

The

rotor

shaft

and

disc

(Figure

2.4)

are

made

of

SAE

4340

steel.

The

hollow

rotor

shaft

and

each

of

the

two

cones

that

make

up

the

disc

are

machined

from

individual

forgings

to

a

0.030"

-

0.060"

envelope,

heat

treated,

and

final

machined

except

for

surfaces

affecting

final

assembly

tolerances.

The

two

cones

are

bolted

together

with

36

tie

bolts

at

the

outside

diameter

to

form

the

rim

of

the

disc.

The

cones

are

shrink-

fitted

to

the

shaft

to

form

a

permanent disc-shaft assembly.

Final

machining

of

assembly

surfaces

and

broaching

of

the

blade

dovetail

slots

completes

the

disc-shaft assembly.

2.6

Blade

Retainer Rings

a.

Each

rotor

assembly

has

two

blade retainer

rings

(Figure

2.4).

The

rings

are

bolted

one

to

each

side

of

the

disc

rim; they

prevent

axial

translation

of

the

blade

dovetails

and

provide

attachment

for

the

blade platforms. The rings

are

formed

of

0.045"

17-7

PH

sheet and

contain

36

holes around

the

circumference

to

accommodate

the tie

bolts.

Thirty-six

equally

spaced

tabs

(stamped

from

0.022"

17-7

PH

sheet) are

spot

welded

to

each

ring;

an

anchor

nut

is

spot

welded

to

each

tab

to

provide

an

attachment

for the

blade

platforms.

2.7

Rotor

Blades

a.

The

rotor

has

36

blades

(Figure

2.4)

which

pump

the air

downward

to

produce

lift.

The

blades

have

a

constant

section airfoil

and

are

made

without

platforms.

Each

blade

is

rough

machined

from

either

an

oversized

1-2.4

)

R-1

forging

or

a

hot

rolled

bar

of heat

treated

PH

14-4

Mo,

stress

relieved,

and

final

machined.

The

dovetail

and

shank

are

milled

and

ground

to

final

dimensions.

A

tang

machined

on

the

blade

tip

provides

a

hole

for

a

attachment

to

the

turbine

bucket

carrier

assembly.

2.8

Blade

Platforms

a.

The rotor

has

3U

blade

platforms (Figure

2.4)

which

form

the

inner

aerodynamic

flow

path

througt

the

fan.

The platforms

and

the

stiffening

braces

are

formed

of

0.028"

61S

aluminum.

The assembly

is

spot

welded,

brazed,

and heat

treated.

Two

bolt

hole

grommets

and

washers

(AMS

5510

stainless

steel)

are

swaged

to

th

platform

assembly.

The

platform

assemblies

are

bolted

to

the

tabs

on

the

recaiLner

rings.

2.9

Torque

Band

Segments

a.

Each

rotor

assembly has

two

sets

of

torque

band

segments

(Figure

2.4),

one

set is

located

on

each

side

of

the

rotor (inlet

and

-xit)

between

the

blade

tips and

the

turbine

bucket

carrier

assembly.

The

segments

transmit

torque

from

the

active

part

of

the

turbine

to

the

blades

which

are out

of

the

partial admission

arc.

Each

torque

band

has

six

segments

formed

of

R41

stainless

steel.

Six

ears

project from

each

segment;

three

of

the ears

contain

two

holes,

the

remaining

three

ears

contain one

hole.

A

grommet,

machined

from

R41

stainless

steel,

is

press-fitted

into

the

single-hole

ear

and

is

positioned

at

the

center

of

each

carrier;

the

bolted

connection

at

this

point establishes rotor

spacing

and transmits

the

torque.

The

two-hole

ears

join

the

ends of

the

carrier segments

and

restrict

axial

displacement;

the

bolt

3izes

and

torquing

standards

allow circumferential

growth

of

the

rotor.

2.10

Carrier

Segment

Seal

a.

The

carrier

segment

seal

(Figure

2.4)

forms

part of

the

outer

[

flow

path

through

the

fan.

The

seal

is

formed

in

two

parts

from

0.045"

R41 stainless

steel.

The

halves

are

welded

together

and

slotted

to

accommodate

two

blade

tip

tangs

and

cover

stands.

The

seals

are

bolted

Z-2.5

R-1

to

the

carrier through

ears

mntching

those

in

the

torque

bands. These

same

bolts

provide

the

means

for

assembly

of

the

carrier,

seal,

cover,

carrier

tab

and

torque

band. The

grommet

used

to

align

the

torque

band

extends

into

the

center

hole

of

each

seal

segment

to

establish location.

2.11

Blade

Shroud

Cover

a.

The

36

blade

shroud covers

(Figure

2.4)

form

the

remainder

of

the

aerodynamic

flow

path

at

the

comprecsor

blade

tips,

provide

an

emergency

torque

transmission

system,

and

carry

self-locking

nuts

to

attach

the

shroud covers

and

the

torque bands

and

seals

to

the

turbine

bucket

carrier.

The blade

shroud covers

are

formed from

0.015"

17-7

PH

sheet,

stress

relieved,

spot

welded

and

heat

treated.

2.12

Blade

Carrier

Pins

a.

The blade

carrier pins

attach

the

blade

tip

tang

to

the

turbine

bucket

carrier.

The

pins are

assembled

by

select

fit

and

are

manufactured

in

five

different

sizes

ranging

from

0.3899"

to

0.3914"

in

increments

of

0.0003". The

pins

(36

to

each

rotor)

are

centerless

ground

to

the

finished

dimensions from

R41

stainless

steel

age

hardened

to

Rc

35

to

43.

A

portion

of

the

diameter

of

the

is

contoured

to

prevent

tang

fretting.

The

blade

carrier

is

drilled

to

receive

a

small

radial

lock

pin.

2.13

Lock

a.

The

lock

prevents

translation

or

rotation

of

the

blade-carrier

during

fan

operation. The

lock

is

machined

to

a

0.115"

to

0.120"

diameter from

403

sta.nless

steel,

Rc

20 to 26

hardness.

2.14

Lock

Strip

a.

The

lock

strip

secures

the

lock

and

holds

it

in

place

during

fan

operation.

The

lock

strip

is

made

of

0.015"

321

stainless

steel sheet

and

has

a

hole

to

receive

the

lock

pin.

1-2.6

2.15

Turbine

Bucket

Carrier

Assembly

a.

The

rotor

assembly

includes

18

turbine

bucket

carrier

assemblies

(Figure

2.4).

Each

turbine bucket

carrier

assembly

(or

segment)

consists

of

18

turbine

buckets,

18

tip

shrouds,

and

a

carrier

brazed

to

form

a

permanent assembly.

2.16

Turbine

Buckets

a.

The

turbine

buckets

are

hollow

shells

formed

to

aerodynamic

shape

fromn

seamless

cylinders

of

0.015"

:nconel

X

stainless

steel.

Each

bucket contains

one

stiffener

rib

running

the

full

length

of the

airfoil

at

mid-chord,

and

two

inserts (one

at

the

leading

edge

and one

at

the

trailing

edge),

and

three

bulkhead

panels

at

the

root

of

the

turbine

bucket.

These

components

are

tweezer

welded

into

a

sub-assembly

and

brazed

prior

to

final

assembly

to

the

turbine bucket

carrier.

2.17

Bucket Tip Shrouds

a.

The

bucket

tip

shrouds limit

tangential

displacement

of

the

bucket

tip,

act

as

a

bucket vibration

damper,

provide

a

radial

seal

against

hot

gas

leakage across

the

bucket

tip

and

form

the

outer

flow

path

for

hot

gas

passing

through

the

turbine.

The

shrouds

are.stamped

from 0.010"

Inconel

X-sheet

ard

are

pierced

with

slots

to

accommodate

the

bucket

tip

airfoil

profile.

The

shrouds

are

brazed

to

the

bucket

tip

during

the

final

brazing

of

the

bucket-carrier

assembly.

2.18

Bucket

Carrier

a.

The

bucket carrier

forms

the

inner

flow

path

through

the

turbine,

supports

the

turbine

buckets

and

provides

the

means

of

attaching

the

tip

turbine,

fen

blades, torque bands,

and

seals.

The

carrier

assembly consists

of

two

side

plates,

a

c.-oss

beam,

a

yoke,

and

a

platform.

b.

The

side

plates

are

the

primary

members

of the

carrier

structure.

They

are

machined

from

Inconel

X

stainless

steel

bar and

have

a

channel

shape

with

tapered

flanges.

1-2.7

GE XV-5A Manual

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